1 00:00:00,000 --> 00:01:14,330 you 2 00:01:14,330 --> 00:01:14,340 3 00:01:14,340 --> 00:01:17,430 at NASA Ames Research Center our basic 4 00:01:17,430 --> 00:01:17,440 at NASA Ames Research Center our basic 5 00:01:17,440 --> 00:01:19,350 at NASA Ames Research Center our basic product is information information is 6 00:01:19,350 --> 00:01:19,360 product is information information is 7 00:01:19,360 --> 00:01:21,600 product is information information is produced in the form of reports 8 00:01:21,600 --> 00:01:21,610 produced in the form of reports 9 00:01:21,610 --> 00:01:24,210 produced in the form of reports technical reports publications and also 10 00:01:24,210 --> 00:01:24,220 technical reports publications and also 11 00:01:24,220 --> 00:01:27,780 technical reports publications and also computer software we export hundreds of 12 00:01:27,780 --> 00:01:27,790 computer software we export hundreds of 13 00:01:27,790 --> 00:01:29,370 computer software we export hundreds of computer programs each year to the 14 00:01:29,370 --> 00:01:29,380 computer programs each year to the 15 00:01:29,380 --> 00:01:31,469 computer programs each year to the aerospace industry to be used by them to 16 00:01:31,469 --> 00:01:31,479 aerospace industry to be used by them to 17 00:01:31,479 --> 00:01:33,360 aerospace industry to be used by them to help them in their design process of 18 00:01:33,360 --> 00:01:33,370 help them in their design process of 19 00:01:33,370 --> 00:01:35,520 help them in their design process of various vehicle components or 20 00:01:35,520 --> 00:01:35,530 various vehicle components or 21 00:01:35,530 --> 00:01:38,010 various vehicle components or configurations the technology developed 22 00:01:38,010 --> 00:01:38,020 configurations the technology developed 23 00:01:38,020 --> 00:01:39,719 configurations the technology developed here at NASA Ames Research Center in the 24 00:01:39,719 --> 00:01:39,729 here at NASA Ames Research Center in the 25 00:01:39,729 --> 00:01:41,520 here at NASA Ames Research Center in the form of computational simulation 26 00:01:41,520 --> 00:01:41,530 form of computational simulation 27 00:01:41,530 --> 00:01:43,109 form of computational simulation software can benefit the aerospace 28 00:01:43,109 --> 00:01:43,119 software can benefit the aerospace 29 00:01:43,119 --> 00:01:46,440 software can benefit the aerospace industry by helping them produce safer 30 00:01:46,440 --> 00:01:46,450 industry by helping them produce safer 31 00:01:46,450 --> 00:01:48,450 industry by helping them produce safer and more fuel-efficient aircraft and 32 00:01:48,450 --> 00:01:48,460 and more fuel-efficient aircraft and 33 00:01:48,460 --> 00:01:50,700 and more fuel-efficient aircraft and also producing those aircraft at a 34 00:01:50,700 --> 00:01:50,710 also producing those aircraft at a 35 00:01:50,710 --> 00:01:51,810 also producing those aircraft at a reduced cost 36 00:01:51,810 --> 00:01:51,820 reduced cost 37 00:01:51,820 --> 00:01:54,630 reduced cost there are basically three aerodynamic 38 00:01:54,630 --> 00:01:54,640 there are basically three aerodynamic 39 00:01:54,640 --> 00:01:57,450 there are basically three aerodynamic simulation scientists that exist there's 40 00:01:57,450 --> 00:01:57,460 simulation scientists that exist there's 41 00:01:57,460 --> 00:02:00,330 simulation scientists that exist there's flight testing there's experimental 42 00:02:00,330 --> 00:02:00,340 flight testing there's experimental 43 00:02:00,340 --> 00:02:02,430 flight testing there's experimental testing and then there's computational 44 00:02:02,430 --> 00:02:02,440 testing and then there's computational 45 00:02:02,440 --> 00:02:04,620 testing and then there's computational fluid dynamics each has its advantages 46 00:02:04,620 --> 00:02:04,630 fluid dynamics each has its advantages 47 00:02:04,630 --> 00:02:08,160 fluid dynamics each has its advantages and disadvantages used together that's 48 00:02:08,160 --> 00:02:08,170 and disadvantages used together that's 49 00:02:08,170 --> 00:02:10,229 and disadvantages used together that's what we call computation to flight which 50 00:02:10,229 --> 00:02:10,239 what we call computation to flight which 51 00:02:10,239 --> 00:02:12,840 what we call computation to flight which is one of the visions at NASA's Ames 52 00:02:12,840 --> 00:02:12,850 is one of the visions at NASA's Ames 53 00:02:12,850 --> 00:02:15,120 is one of the visions at NASA's Ames Research Center computational fluid 54 00:02:15,120 --> 00:02:15,130 Research Center computational fluid 55 00:02:15,130 --> 00:02:17,790 Research Center computational fluid dynamics is used to complement both 56 00:02:17,790 --> 00:02:17,800 dynamics is used to complement both 57 00:02:17,800 --> 00:02:20,820 dynamics is used to complement both experimental and flight testing we can 58 00:02:20,820 --> 00:02:20,830 experimental and flight testing we can 59 00:02:20,830 --> 00:02:22,680 experimental and flight testing we can sometimes use computational fluid 60 00:02:22,680 --> 00:02:22,690 sometimes use computational fluid 61 00:02:22,690 --> 00:02:25,410 sometimes use computational fluid dynamics to do smart experimental 62 00:02:25,410 --> 00:02:25,420 dynamics to do smart experimental 63 00:02:25,420 --> 00:02:27,120 dynamics to do smart experimental testing in other words eliminate the 64 00:02:27,120 --> 00:02:27,130 testing in other words eliminate the 65 00:02:27,130 --> 00:02:28,949 testing in other words eliminate the need for doing a lot of repetitive 66 00:02:28,949 --> 00:02:28,959 need for doing a lot of repetitive 67 00:02:28,959 --> 00:02:31,890 need for doing a lot of repetitive testing and only test at very important 68 00:02:31,890 --> 00:02:31,900 testing and only test at very important 69 00:02:31,900 --> 00:02:34,680 testing and only test at very important or very critical test conditions we can 70 00:02:34,680 --> 00:02:34,690 or very critical test conditions we can 71 00:02:34,690 --> 00:02:36,780 or very critical test conditions we can do the same thing with flight testing as 72 00:02:36,780 --> 00:02:36,790 do the same thing with flight testing as 73 00:02:36,790 --> 00:02:38,190 do the same thing with flight testing as you know flight testing is a very 74 00:02:38,190 --> 00:02:38,200 you know flight testing is a very 75 00:02:38,200 --> 00:02:40,320 you know flight testing is a very expensive process we can use 76 00:02:40,320 --> 00:02:40,330 expensive process we can use 77 00:02:40,330 --> 00:02:43,320 expensive process we can use computational fluid dynamics to help 78 00:02:43,320 --> 00:02:43,330 computational fluid dynamics to help 79 00:02:43,330 --> 00:02:45,330 computational fluid dynamics to help augment that testing program and the 80 00:02:45,330 --> 00:02:45,340 augment that testing program and the 81 00:02:45,340 --> 00:02:47,759 augment that testing program and the data that it's produced the computers 82 00:02:47,759 --> 00:02:47,769 data that it's produced the computers 83 00:02:47,769 --> 00:02:49,170 data that it's produced the computers that are used to generate some of the 84 00:02:49,170 --> 00:02:49,180 that are used to generate some of the 85 00:02:49,180 --> 00:02:51,150 that are used to generate some of the results that you see today are contained 86 00:02:51,150 --> 00:02:51,160 results that you see today are contained 87 00:02:51,160 --> 00:02:52,650 results that you see today are contained in our NASA building the numerical 88 00:02:52,650 --> 00:02:52,660 in our NASA building the numerical 89 00:02:52,660 --> 00:02:54,780 in our NASA building the numerical aerodynamic simulation facility they 90 00:02:54,780 --> 00:02:54,790 aerodynamic simulation facility they 91 00:02:54,790 --> 00:02:57,270 aerodynamic simulation facility they included a crate to computer and a Cray 92 00:02:57,270 --> 00:02:57,280 included a crate to computer and a Cray 93 00:02:57,280 --> 00:02:59,430 included a crate to computer and a Cray ymp computer these are two of the 94 00:02:59,430 --> 00:02:59,440 ymp computer these are two of the 95 00:02:59,440 --> 00:03:02,160 ymp computer these are two of the fastest computers in the world today the 96 00:03:02,160 --> 00:03:02,170 fastest computers in the world today the 97 00:03:02,170 --> 00:03:04,470 fastest computers in the world today the process by which we perform CFD 98 00:03:04,470 --> 00:03:04,480 process by which we perform CFD 99 00:03:04,480 --> 00:03:06,470 process by which we perform CFD simulations involves first of all 100 00:03:06,470 --> 00:03:06,480 simulations involves first of all 101 00:03:06,480 --> 00:03:08,910 simulations involves first of all defining the geometry forgetting 102 00:03:08,910 --> 00:03:08,920 defining the geometry forgetting 103 00:03:08,920 --> 00:03:11,190 defining the geometry forgetting that geometry into the computer the next 104 00:03:11,190 --> 00:03:11,200 that geometry into the computer the next 105 00:03:11,200 --> 00:03:12,930 that geometry into the computer the next step involves discretizing the flow 106 00:03:12,930 --> 00:03:12,940 step involves discretizing the flow 107 00:03:12,940 --> 00:03:15,570 step involves discretizing the flow field about that configuration once that 108 00:03:15,570 --> 00:03:15,580 field about that configuration once that 109 00:03:15,580 --> 00:03:17,190 field about that configuration once that flow field is discretized then we can 110 00:03:17,190 --> 00:03:17,200 flow field is discretized then we can 111 00:03:17,200 --> 00:03:19,589 flow field is discretized then we can apply a flow solver in order to compute 112 00:03:19,589 --> 00:03:19,599 apply a flow solver in order to compute 113 00:03:19,599 --> 00:03:22,740 apply a flow solver in order to compute the flow about that configuration that's 114 00:03:22,740 --> 00:03:22,750 the flow about that configuration that's 115 00:03:22,750 --> 00:03:24,870 the flow about that configuration that's generates an enormous amount of data and 116 00:03:24,870 --> 00:03:24,880 generates an enormous amount of data and 117 00:03:24,880 --> 00:03:28,440 generates an enormous amount of data and we use graphics workstations to reduce 118 00:03:28,440 --> 00:03:28,450 we use graphics workstations to reduce 119 00:03:28,450 --> 00:03:32,250 we use graphics workstations to reduce that data and produce the results once 120 00:03:32,250 --> 00:03:32,260 that data and produce the results once 121 00:03:32,260 --> 00:03:33,930 that data and produce the results once that technology has been validated 122 00:03:33,930 --> 00:03:33,940 that technology has been validated 123 00:03:33,940 --> 00:03:36,390 that technology has been validated against experimental data and we 124 00:03:36,390 --> 00:03:36,400 against experimental data and we 125 00:03:36,400 --> 00:03:38,070 against experimental data and we disseminate that technology for 126 00:03:38,070 --> 00:03:38,080 disseminate that technology for 127 00:03:38,080 --> 00:03:50,309 disseminate that technology for industries use during launch of the 128 00:03:50,309 --> 00:03:50,319 industries use during launch of the 129 00:03:50,319 --> 00:03:52,620 industries use during launch of the space shuttle provisions have been made 130 00:03:52,620 --> 00:03:52,630 space shuttle provisions have been made 131 00:03:52,630 --> 00:03:54,990 space shuttle provisions have been made to employ an abort mode in case of 132 00:03:54,990 --> 00:03:55,000 to employ an abort mode in case of 133 00:03:55,000 --> 00:03:57,780 to employ an abort mode in case of emergency one of the elements of this 134 00:03:57,780 --> 00:03:57,790 emergency one of the elements of this 135 00:03:57,790 --> 00:04:01,320 emergency one of the elements of this abort mode is known as fast step fast 136 00:04:01,320 --> 00:04:01,330 abort mode is known as fast step fast 137 00:04:01,330 --> 00:04:03,930 abort mode is known as fast step fast SEP is the fast separation of Shuttle 138 00:04:03,930 --> 00:04:03,940 SEP is the fast separation of Shuttle 139 00:04:03,940 --> 00:04:05,370 SEP is the fast separation of Shuttle Orbiter from the rest of the launch 140 00:04:05,370 --> 00:04:05,380 Orbiter from the rest of the launch 141 00:04:05,380 --> 00:04:08,250 Orbiter from the rest of the launch vehicle as the shuttle goes through the 142 00:04:08,250 --> 00:04:08,260 vehicle as the shuttle goes through the 143 00:04:08,260 --> 00:04:10,110 vehicle as the shuttle goes through the launch sequence we will look at the 144 00:04:10,110 --> 00:04:10,120 launch sequence we will look at the 145 00:04:10,120 --> 00:04:11,840 launch sequence we will look at the results of two different numerical 146 00:04:11,840 --> 00:04:11,850 results of two different numerical 147 00:04:11,850 --> 00:04:15,000 results of two different numerical simulations the first occurs during 148 00:04:15,000 --> 00:04:15,010 simulations the first occurs during 149 00:04:15,010 --> 00:04:18,300 simulations the first occurs during ascent as the shuttle passes through the 150 00:04:18,300 --> 00:04:18,310 ascent as the shuttle passes through the 151 00:04:18,310 --> 00:04:21,360 ascent as the shuttle passes through the transonic range the external tanks of 152 00:04:21,360 --> 00:04:21,370 transonic range the external tanks of 153 00:04:21,370 --> 00:04:23,070 transonic range the external tanks of the rocket motors experience a 154 00:04:23,070 --> 00:04:23,080 the rocket motors experience a 155 00:04:23,080 --> 00:04:25,760 the rocket motors experience a hysteresis effect due to shock movement 156 00:04:25,760 --> 00:04:25,770 hysteresis effect due to shock movement 157 00:04:25,770 --> 00:04:28,380 hysteresis effect due to shock movement since the Mach number is changing from 158 00:04:28,380 --> 00:04:28,390 since the Mach number is changing from 159 00:04:28,390 --> 00:04:32,310 since the Mach number is changing from 0.8 to 1.0 to over 6 seconds as shown 160 00:04:32,310 --> 00:04:32,320 0.8 to 1.0 to over 6 seconds as shown 161 00:04:32,320 --> 00:04:34,980 0.8 to 1.0 to over 6 seconds as shown here the unsteady flow field that 162 00:04:34,980 --> 00:04:34,990 here the unsteady flow field that 163 00:04:34,990 --> 00:04:37,620 here the unsteady flow field that evolves around the vehicle lags behind 164 00:04:37,620 --> 00:04:37,630 evolves around the vehicle lags behind 165 00:04:37,630 --> 00:04:40,080 evolves around the vehicle lags behind what it would be for steady flow or a 166 00:04:40,080 --> 00:04:40,090 what it would be for steady flow or a 167 00:04:40,090 --> 00:04:53,280 what it would be for steady flow or a fixed Mach number 168 00:04:53,280 --> 00:04:53,290 169 00:04:53,290 --> 00:04:55,920 notice the shock development shown by 170 00:04:55,920 --> 00:04:55,930 notice the shock development shown by 171 00:04:55,930 --> 00:04:57,630 notice the shock development shown by the pressure contours on the leading 172 00:04:57,630 --> 00:04:57,640 the pressure contours on the leading 173 00:04:57,640 --> 00:05:28,650 the pressure contours on the leading surface of the tank 174 00:05:28,650 --> 00:05:28,660 175 00:05:28,660 --> 00:05:31,920 on the base of the tank we see a highly 176 00:05:31,920 --> 00:05:31,930 on the base of the tank we see a highly 177 00:05:31,930 --> 00:05:58,260 on the base of the tank we see a highly unstable flow regime 178 00:05:58,260 --> 00:05:58,270 179 00:05:58,270 --> 00:06:01,080 the second numerical simulation occurs 180 00:06:01,080 --> 00:06:01,090 the second numerical simulation occurs 181 00:06:01,090 --> 00:06:03,150 the second numerical simulation occurs at about two minutes into the flight at 182 00:06:03,150 --> 00:06:03,160 at about two minutes into the flight at 183 00:06:03,160 --> 00:06:06,900 at about two minutes into the flight at an elevation of about 50,000 meters at 184 00:06:06,900 --> 00:06:06,910 an elevation of about 50,000 meters at 185 00:06:06,910 --> 00:06:09,600 an elevation of about 50,000 meters at this time the solid rocket boosters or 186 00:06:09,600 --> 00:06:09,610 this time the solid rocket boosters or 187 00:06:09,610 --> 00:06:12,180 this time the solid rocket boosters or SRBs fall away from the tank and the 188 00:06:12,180 --> 00:06:12,190 SRBs fall away from the tank and the 189 00:06:12,190 --> 00:06:15,390 SRBs fall away from the tank and the orbiter these bodies moving relative to 190 00:06:15,390 --> 00:06:15,400 orbiter these bodies moving relative to 191 00:06:15,400 --> 00:06:17,999 orbiter these bodies moving relative to each other make analysis using other 192 00:06:17,999 --> 00:06:18,009 each other make analysis using other 193 00:06:18,009 --> 00:06:22,129 each other make analysis using other methods much more difficult 194 00:06:22,129 --> 00:06:22,139 195 00:06:22,139 --> 00:06:24,570 notice the interaction of the pressure 196 00:06:24,570 --> 00:06:24,580 notice the interaction of the pressure 197 00:06:24,580 --> 00:06:28,499 notice the interaction of the pressure contours as separation occurs visible 198 00:06:28,499 --> 00:06:28,509 contours as separation occurs visible 199 00:06:28,509 --> 00:06:30,570 contours as separation occurs visible under the body of the shuttle are the 200 00:06:30,570 --> 00:06:30,580 under the body of the shuttle are the 201 00:06:30,580 --> 00:06:32,640 under the body of the shuttle are the pressure contours created by shockwave 202 00:06:32,640 --> 00:06:32,650 pressure contours created by shockwave 203 00:06:32,650 --> 00:06:35,610 pressure contours created by shockwave interaction between the orbiter the 204 00:06:35,610 --> 00:06:35,620 interaction between the orbiter the 205 00:06:35,620 --> 00:06:41,570 interaction between the orbiter the external tank and the SRBs 206 00:06:41,570 --> 00:06:41,580 207 00:06:41,580 --> 00:06:44,700 Robert mecan research scientist and 208 00:06:44,700 --> 00:06:44,710 Robert mecan research scientist and 209 00:06:44,710 --> 00:06:46,740 Robert mecan research scientist and member of the NASA Ames space shuttle 210 00:06:46,740 --> 00:06:46,750 member of the NASA Ames space shuttle 211 00:06:46,750 --> 00:06:49,680 member of the NASA Ames space shuttle flow simulation team explains the work 212 00:06:49,680 --> 00:06:49,690 flow simulation team explains the work 213 00:06:49,690 --> 00:06:52,710 flow simulation team explains the work done with a solid rocket booster or SRB 214 00:06:52,710 --> 00:06:52,720 done with a solid rocket booster or SRB 215 00:06:52,720 --> 00:06:55,740 done with a solid rocket booster or SRB as a stepping stone to simulating fast 216 00:06:55,740 --> 00:06:55,750 as a stepping stone to simulating fast 217 00:06:55,750 --> 00:06:58,649 as a stepping stone to simulating fast set K the work that the Space Shuttle 218 00:06:58,649 --> 00:06:58,659 set K the work that the Space Shuttle 219 00:06:58,659 --> 00:07:02,370 set K the work that the Space Shuttle Group at Ames they interact with the 220 00:07:02,370 --> 00:07:02,380 Group at Ames they interact with the 221 00:07:02,380 --> 00:07:05,939 Group at Ames they interact with the Johnson Space Center and we're doing 222 00:07:05,939 --> 00:07:05,949 Johnson Space Center and we're doing 223 00:07:05,949 --> 00:07:07,860 Johnson Space Center and we're doing numerical simulations of various 224 00:07:07,860 --> 00:07:07,870 numerical simulations of various 225 00:07:07,870 --> 00:07:09,839 numerical simulations of various conditions of the shuttle during during 226 00:07:09,839 --> 00:07:09,849 conditions of the shuttle during during 227 00:07:09,849 --> 00:07:12,510 conditions of the shuttle during during the ascent of course there's a great 228 00:07:12,510 --> 00:07:12,520 the ascent of course there's a great 229 00:07:12,520 --> 00:07:14,219 the ascent of course there's a great deal of wind tunnel data that's 230 00:07:14,219 --> 00:07:14,229 deal of wind tunnel data that's 231 00:07:14,229 --> 00:07:16,290 deal of wind tunnel data that's available and also flight data that's 232 00:07:16,290 --> 00:07:16,300 available and also flight data that's 233 00:07:16,300 --> 00:07:20,219 available and also flight data that's been accumulated over the flight history 234 00:07:20,219 --> 00:07:20,229 been accumulated over the flight history 235 00:07:20,229 --> 00:07:23,249 been accumulated over the flight history of the shuttle and the shuttle group 236 00:07:23,249 --> 00:07:23,259 of the shuttle and the shuttle group 237 00:07:23,259 --> 00:07:25,680 of the shuttle and the shuttle group here at Ames is augmenting the data that 238 00:07:25,680 --> 00:07:25,690 here at Ames is augmenting the data that 239 00:07:25,690 --> 00:07:27,510 here at Ames is augmenting the data that there is they're filling in missing data 240 00:07:27,510 --> 00:07:27,520 there is they're filling in missing data 241 00:07:27,520 --> 00:07:29,640 there is they're filling in missing data and carrying out calculations that 242 00:07:29,640 --> 00:07:29,650 and carrying out calculations that 243 00:07:29,650 --> 00:07:31,890 and carrying out calculations that really aren't possible to model in any 244 00:07:31,890 --> 00:07:31,900 really aren't possible to model in any 245 00:07:31,900 --> 00:07:34,680 really aren't possible to model in any other way path SEP being one of those 246 00:07:34,680 --> 00:07:34,690 other way path SEP being one of those 247 00:07:34,690 --> 00:07:36,809 other way path SEP being one of those cases but really there's no other way to 248 00:07:36,809 --> 00:07:36,819 cases but really there's no other way to 249 00:07:36,819 --> 00:07:46,060 cases but really there's no other way to get that sort of information 250 00:07:46,060 --> 00:07:46,070 251 00:07:46,070 --> 00:07:48,230 Computers now have primary controller 252 00:07:48,230 --> 00:07:48,240 Computers now have primary controller 253 00:07:48,240 --> 00:07:50,270 Computers now have primary controller critics like turbo pump is the main 254 00:07:50,270 --> 00:07:50,280 critics like turbo pump is the main 255 00:07:50,280 --> 00:07:52,400 critics like turbo pump is the main element in a rocket engine that supplies 256 00:07:52,400 --> 00:07:52,410 element in a rocket engine that supplies 257 00:07:52,410 --> 00:07:54,350 element in a rocket engine that supplies fuel from the fuel tank to the 258 00:07:54,350 --> 00:07:54,360 fuel from the fuel tank to the 259 00:07:54,360 --> 00:07:57,350 fuel from the fuel tank to the combustion chamber an important 260 00:07:57,350 --> 00:07:57,360 combustion chamber an important 261 00:07:57,360 --> 00:07:59,000 combustion chamber an important component in the turbo pump is the 262 00:07:59,000 --> 00:07:59,010 component in the turbo pump is the 263 00:07:59,010 --> 00:08:02,870 component in the turbo pump is the inducer a massive flow separation or 264 00:08:02,870 --> 00:08:02,880 inducer a massive flow separation or 265 00:08:02,880 --> 00:08:05,660 inducer a massive flow separation or cavitation in the inducer can block the 266 00:08:05,660 --> 00:08:05,670 cavitation in the inducer can block the 267 00:08:05,670 --> 00:08:08,600 cavitation in the inducer can block the fuel supply and result in total engine 268 00:08:08,600 --> 00:08:08,610 fuel supply and result in total engine 269 00:08:08,610 --> 00:08:19,580 fuel supply and result in total engine failure see kwan-yuen a senior research 270 00:08:19,580 --> 00:08:19,590 failure see kwan-yuen a senior research 271 00:08:19,590 --> 00:08:22,070 failure see kwan-yuen a senior research scientist of mcat institute at ames 272 00:08:22,070 --> 00:08:22,080 scientist of mcat institute at ames 273 00:08:22,080 --> 00:08:25,400 scientist of mcat institute at ames research center explains a computational 274 00:08:25,400 --> 00:08:25,410 research center explains a computational 275 00:08:25,410 --> 00:08:27,560 research center explains a computational study of this kind of problem was 276 00:08:27,560 --> 00:08:27,570 study of this kind of problem was 277 00:08:27,570 --> 00:08:31,550 study of this kind of problem was impractical even on supercomputers since 278 00:08:31,550 --> 00:08:31,560 impractical even on supercomputers since 279 00:08:31,560 --> 00:08:33,500 impractical even on supercomputers since the existing computer programs were not 280 00:08:33,500 --> 00:08:33,510 the existing computer programs were not 281 00:08:33,510 --> 00:08:36,560 the existing computer programs were not fast enough the objective of our project 282 00:08:36,560 --> 00:08:36,570 fast enough the objective of our project 283 00:08:36,570 --> 00:08:39,080 fast enough the objective of our project is to develop a very efficient computer 284 00:08:39,080 --> 00:08:39,090 is to develop a very efficient computer 285 00:08:39,090 --> 00:08:41,510 is to develop a very efficient computer program which can give a direct impact 286 00:08:41,510 --> 00:08:41,520 program which can give a direct impact 287 00:08:41,520 --> 00:08:44,500 program which can give a direct impact on the design of future rocket engines 288 00:08:44,500 --> 00:08:44,510 on the design of future rocket engines 289 00:08:44,510 --> 00:08:47,780 on the design of future rocket engines shown here is the actual hardware of the 290 00:08:47,780 --> 00:08:47,790 shown here is the actual hardware of the 291 00:08:47,790 --> 00:08:50,720 shown here is the actual hardware of the space shuttle main engine the turbo pump 292 00:08:50,720 --> 00:08:50,730 space shuttle main engine the turbo pump 293 00:08:50,730 --> 00:08:53,420 space shuttle main engine the turbo pump consists of an inducer with a stationary 294 00:08:53,420 --> 00:08:53,430 consists of an inducer with a stationary 295 00:08:53,430 --> 00:08:55,430 consists of an inducer with a stationary casing and a shrouded impeller with 296 00:08:55,430 --> 00:08:55,440 casing and a shrouded impeller with 297 00:08:55,440 --> 00:09:01,820 casing and a shrouded impeller with partial blades in this 298 00:09:01,820 --> 00:09:01,830 partial blades in this 299 00:09:01,830 --> 00:09:04,670 partial blades in this computer-generated image we remove the 300 00:09:04,670 --> 00:09:04,680 computer-generated image we remove the 301 00:09:04,680 --> 00:09:06,980 computer-generated image we remove the shroud and view the inducer and partial 302 00:09:06,980 --> 00:09:06,990 shroud and view the inducer and partial 303 00:09:06,990 --> 00:09:08,780 shroud and view the inducer and partial blades of the impeller 304 00:09:08,780 --> 00:09:08,790 blades of the impeller 305 00:09:08,790 --> 00:09:11,730 blades of the impeller we can see a pressure gradient across 306 00:09:11,730 --> 00:09:11,740 we can see a pressure gradient across 307 00:09:11,740 --> 00:09:14,520 we can see a pressure gradient across the blades as well as along the hub due 308 00:09:14,520 --> 00:09:14,530 the blades as well as along the hub due 309 00:09:14,530 --> 00:09:21,990 the blades as well as along the hub due to the action of the centrifugal force 310 00:09:21,990 --> 00:09:22,000 311 00:09:22,000 --> 00:09:24,840 the particle traces over the suction 312 00:09:24,840 --> 00:09:24,850 the particle traces over the suction 313 00:09:24,850 --> 00:09:26,759 the particle traces over the suction side of the blade and through the tip 314 00:09:26,759 --> 00:09:26,769 side of the blade and through the tip 315 00:09:26,769 --> 00:09:29,819 side of the blade and through the tip clearance are seen here particles over 316 00:09:29,819 --> 00:09:29,829 clearance are seen here particles over 317 00:09:29,829 --> 00:09:31,800 clearance are seen here particles over the pressure side of the blade shown in 318 00:09:31,800 --> 00:09:31,810 the pressure side of the blade shown in 319 00:09:31,810 --> 00:09:34,439 the pressure side of the blade shown in purple are sucked into the tip clearance 320 00:09:34,439 --> 00:09:34,449 purple are sucked into the tip clearance 321 00:09:34,449 --> 00:09:38,519 purple are sucked into the tip clearance and become the leakage flow the 322 00:09:38,519 --> 00:09:38,529 and become the leakage flow the 323 00:09:38,529 --> 00:09:40,949 and become the leakage flow the streamwise particle flow is shown in 324 00:09:40,949 --> 00:09:40,959 streamwise particle flow is shown in 325 00:09:40,959 --> 00:09:45,420 streamwise particle flow is shown in green the interaction of the leakage and 326 00:09:45,420 --> 00:09:45,430 green the interaction of the leakage and 327 00:09:45,430 --> 00:09:48,509 green the interaction of the leakage and screen wise flows results in a region of 328 00:09:48,509 --> 00:09:48,519 screen wise flows results in a region of 329 00:09:48,519 --> 00:09:57,980 screen wise flows results in a region of concentrated vorticity dough john kwok 330 00:09:57,980 --> 00:09:57,990 concentrated vorticity dough john kwok 331 00:09:57,990 --> 00:10:00,179 concentrated vorticity dough john kwok research scientist with the applied 332 00:10:00,179 --> 00:10:00,189 research scientist with the applied 333 00:10:00,189 --> 00:10:02,280 research scientist with the applied computation of fluids branch of Ames 334 00:10:02,280 --> 00:10:02,290 computation of fluids branch of Ames 335 00:10:02,290 --> 00:10:04,379 computation of fluids branch of Ames Research Center and group leader for 336 00:10:04,379 --> 00:10:04,389 Research Center and group leader for 337 00:10:04,389 --> 00:10:07,230 Research Center and group leader for this project continues the explanation 338 00:10:07,230 --> 00:10:07,240 this project continues the explanation 339 00:10:07,240 --> 00:10:10,769 this project continues the explanation power pump is especially one key area we 340 00:10:10,769 --> 00:10:10,779 power pump is especially one key area we 341 00:10:10,779 --> 00:10:13,889 power pump is especially one key area we can improve the performance aircraft 342 00:10:13,889 --> 00:10:13,899 can improve the performance aircraft 343 00:10:13,899 --> 00:10:16,860 can improve the performance aircraft engine normally performs in the 344 00:10:16,860 --> 00:10:16,870 engine normally performs in the 345 00:10:16,870 --> 00:10:19,309 engine normally performs in the efficiencies in the 90 percentile range 346 00:10:19,309 --> 00:10:19,319 efficiencies in the 90 percentile range 347 00:10:19,319 --> 00:10:22,439 efficiencies in the 90 percentile range typically total pumper operates in 80 348 00:10:22,439 --> 00:10:22,449 typically total pumper operates in 80 349 00:10:22,449 --> 00:10:25,679 typically total pumper operates in 80 percentile efficiency range so there 350 00:10:25,679 --> 00:10:25,689 percentile efficiency range so there 351 00:10:25,689 --> 00:10:28,410 percentile efficiency range so there suddenly we can see lots of room to 352 00:10:28,410 --> 00:10:28,420 suddenly we can see lots of room to 353 00:10:28,420 --> 00:10:32,280 suddenly we can see lots of room to improve so shuttle can be benefited by 354 00:10:32,280 --> 00:10:32,290 improve so shuttle can be benefited by 355 00:10:32,290 --> 00:10:37,019 improve so shuttle can be benefited by this computational simulation and by 356 00:10:37,019 --> 00:10:37,029 this computational simulation and by 357 00:10:37,029 --> 00:10:39,059 this computational simulation and by improving the performance and improving 358 00:10:39,059 --> 00:10:39,069 improving the performance and improving 359 00:10:39,069 --> 00:10:42,540 improving the performance and improving their reliability and eventually we will 360 00:10:42,540 --> 00:10:42,550 their reliability and eventually we will 361 00:10:42,550 --> 00:10:44,490 their reliability and eventually we will meet the high launch capability in the 362 00:10:44,490 --> 00:10:44,500 meet the high launch capability in the 363 00:10:44,500 --> 00:10:54,550 meet the high launch capability in the future 364 00:10:54,550 --> 00:10:54,560 365 00:10:54,560 --> 00:10:57,590 recent advances in heart surgery have 366 00:10:57,590 --> 00:10:57,600 recent advances in heart surgery have 367 00:10:57,600 --> 00:10:59,510 recent advances in heart surgery have led to the development of the artificial 368 00:10:59,510 --> 00:10:59,520 led to the development of the artificial 369 00:10:59,520 --> 00:11:01,820 led to the development of the artificial heart and the use of artificial heart 370 00:11:01,820 --> 00:11:01,830 heart and the use of artificial heart 371 00:11:01,830 --> 00:11:05,000 heart and the use of artificial heart valves at the same time technology 372 00:11:05,000 --> 00:11:05,010 valves at the same time technology 373 00:11:05,010 --> 00:11:07,130 valves at the same time technology developed to compute the flow in 374 00:11:07,130 --> 00:11:07,140 developed to compute the flow in 375 00:11:07,140 --> 00:11:08,870 developed to compute the flow in components of the space shuttle main 376 00:11:08,870 --> 00:11:08,880 components of the space shuttle main 377 00:11:08,880 --> 00:11:11,780 components of the space shuttle main engine is being applied to simulate the 378 00:11:11,780 --> 00:11:11,790 engine is being applied to simulate the 379 00:11:11,790 --> 00:11:13,940 engine is being applied to simulate the unsteady flow in the Penn State 380 00:11:13,940 --> 00:11:13,950 unsteady flow in the Penn State 381 00:11:13,950 --> 00:11:18,470 unsteady flow in the Penn State artificial heart Joe John Kwok explains 382 00:11:18,470 --> 00:11:18,480 artificial heart Joe John Kwok explains 383 00:11:18,480 --> 00:11:20,600 artificial heart Joe John Kwok explains NASA's involvement in this spin-off 384 00:11:20,600 --> 00:11:20,610 NASA's involvement in this spin-off 385 00:11:20,610 --> 00:11:23,810 NASA's involvement in this spin-off technology in general we are interested 386 00:11:23,810 --> 00:11:23,820 technology in general we are interested 387 00:11:23,820 --> 00:11:26,360 technology in general we are interested in reapplying NASA develop technology 388 00:11:26,360 --> 00:11:26,370 in reapplying NASA develop technology 389 00:11:26,370 --> 00:11:29,150 in reapplying NASA develop technology especially the CFD technology can be 390 00:11:29,150 --> 00:11:29,160 especially the CFD technology can be 391 00:11:29,160 --> 00:11:31,460 especially the CFD technology can be reapplied in many different instances 392 00:11:31,460 --> 00:11:31,470 reapplied in many different instances 393 00:11:31,470 --> 00:11:34,220 reapplied in many different instances and artificial heart is that it it's 394 00:11:34,220 --> 00:11:34,230 and artificial heart is that it it's 395 00:11:34,230 --> 00:11:36,560 and artificial heart is that it it's particularly interesting because it will 396 00:11:36,560 --> 00:11:36,570 particularly interesting because it will 397 00:11:36,570 --> 00:11:39,140 particularly interesting because it will help national health problem and the 398 00:11:39,140 --> 00:11:39,150 help national health problem and the 399 00:11:39,150 --> 00:11:41,270 help national health problem and the demand for this type of mechanical 400 00:11:41,270 --> 00:11:41,280 demand for this type of mechanical 401 00:11:41,280 --> 00:11:46,310 demand for this type of mechanical device can really contribute to to human 402 00:11:46,310 --> 00:11:46,320 device can really contribute to to human 403 00:11:46,320 --> 00:11:48,260 device can really contribute to to human health and also animal health in the 404 00:11:48,260 --> 00:11:48,270 health and also animal health in the 405 00:11:48,270 --> 00:11:49,480 health and also animal health in the future 406 00:11:49,480 --> 00:11:49,490 future 407 00:11:49,490 --> 00:11:52,580 future Chetan Kyra's and Stuart Rogers research 408 00:11:52,580 --> 00:11:52,590 Chetan Kyra's and Stuart Rogers research 409 00:11:52,590 --> 00:11:54,860 Chetan Kyra's and Stuart Rogers research scientists were responsible for the flow 410 00:11:54,860 --> 00:11:54,870 scientists were responsible for the flow 411 00:11:54,870 --> 00:11:56,140 scientists were responsible for the flow code on this project 412 00:11:56,140 --> 00:11:56,150 code on this project 413 00:11:56,150 --> 00:11:59,390 code on this project Stewart Rogers further explains the data 414 00:11:59,390 --> 00:11:59,400 Stewart Rogers further explains the data 415 00:11:59,400 --> 00:12:01,340 Stewart Rogers further explains the data we started with in this case was 416 00:12:01,340 --> 00:12:01,350 we started with in this case was 417 00:12:01,350 --> 00:12:02,990 we started with in this case was basically taken straight off of 418 00:12:02,990 --> 00:12:03,000 basically taken straight off of 419 00:12:03,000 --> 00:12:04,580 basically taken straight off of blueprints which were used to build 420 00:12:04,580 --> 00:12:04,590 blueprints which were used to build 421 00:12:04,590 --> 00:12:07,760 blueprints which were used to build models of this heart which were tested 422 00:12:07,760 --> 00:12:07,770 models of this heart which were tested 423 00:12:07,770 --> 00:12:10,910 models of this heart which were tested by Penn State given the blueprints from 424 00:12:10,910 --> 00:12:10,920 by Penn State given the blueprints from 425 00:12:10,920 --> 00:12:15,200 by Penn State given the blueprints from that model we then generated a series of 426 00:12:15,200 --> 00:12:15,210 that model we then generated a series of 427 00:12:15,210 --> 00:12:18,170 that model we then generated a series of codes which would then describe that 428 00:12:18,170 --> 00:12:18,180 codes which would then describe that 429 00:12:18,180 --> 00:12:20,180 codes which would then describe that shape to the computer as a series of 430 00:12:20,180 --> 00:12:20,190 shape to the computer as a series of 431 00:12:20,190 --> 00:12:22,400 shape to the computer as a series of discrete points once we had those 432 00:12:22,400 --> 00:12:22,410 discrete points once we had those 433 00:12:22,410 --> 00:12:24,230 discrete points once we had those discrete points then our flow solver 434 00:12:24,230 --> 00:12:24,240 discrete points then our flow solver 435 00:12:24,240 --> 00:12:26,600 discrete points then our flow solver could take them and compute the flow 436 00:12:26,600 --> 00:12:26,610 could take them and compute the flow 437 00:12:26,610 --> 00:12:39,310 could take them and compute the flow inside the heart 438 00:12:39,310 --> 00:12:39,320 439 00:12:39,320 --> 00:12:41,900 here we see the main chamber of the 440 00:12:41,900 --> 00:12:41,910 here we see the main chamber of the 441 00:12:41,910 --> 00:12:43,639 here we see the main chamber of the heart and the particle traces which 442 00:12:43,639 --> 00:12:43,649 heart and the particle traces which 443 00:12:43,649 --> 00:12:46,579 heart and the particle traces which indicate the flow the color of the 444 00:12:46,579 --> 00:12:46,589 indicate the flow the color of the 445 00:12:46,589 --> 00:12:49,040 indicate the flow the color of the traces indicates the release height at 446 00:12:49,040 --> 00:12:49,050 traces indicates the release height at 447 00:12:49,050 --> 00:13:07,490 traces indicates the release height at the inflow valve opening this is the 448 00:13:07,490 --> 00:13:07,500 the inflow valve opening this is the 449 00:13:07,500 --> 00:13:09,740 the inflow valve opening this is the computer-generated image of the tilting 450 00:13:09,740 --> 00:13:09,750 computer-generated image of the tilting 451 00:13:09,750 --> 00:13:13,040 computer-generated image of the tilting disk heart valve this valve can be used 452 00:13:13,040 --> 00:13:13,050 disk heart valve this valve can be used 453 00:13:13,050 --> 00:13:14,900 disk heart valve this valve can be used in conjunction with an artificial heart 454 00:13:14,900 --> 00:13:14,910 in conjunction with an artificial heart 455 00:13:14,910 --> 00:13:19,970 in conjunction with an artificial heart or used as a separate device the inflow 456 00:13:19,970 --> 00:13:19,980 or used as a separate device the inflow 457 00:13:19,980 --> 00:13:22,220 or used as a separate device the inflow conditions are specified at the entrance 458 00:13:22,220 --> 00:13:22,230 conditions are specified at the entrance 459 00:13:22,230 --> 00:13:24,320 conditions are specified at the entrance for the valve opening and they are 460 00:13:24,320 --> 00:13:24,330 for the valve opening and they are 461 00:13:24,330 --> 00:13:26,300 for the valve opening and they are specified at the exit for the valve 462 00:13:26,300 --> 00:13:26,310 specified at the exit for the valve 463 00:13:26,310 --> 00:13:30,470 specified at the exit for the valve closing the tilting disk reacts from the 464 00:13:30,470 --> 00:13:30,480 closing the tilting disk reacts from the 465 00:13:30,480 --> 00:13:33,100 closing the tilting disk reacts from the force is applied to it by the blood flow 466 00:13:33,100 --> 00:13:33,110 force is applied to it by the blood flow 467 00:13:33,110 --> 00:13:36,199 force is applied to it by the blood flow the valve motion is made possible by 468 00:13:36,199 --> 00:13:36,209 the valve motion is made possible by 469 00:13:36,209 --> 00:13:38,600 the valve motion is made possible by using the chimera grid embedding 470 00:13:38,600 --> 00:13:38,610 using the chimera grid embedding 471 00:13:38,610 --> 00:13:45,610 using the chimera grid embedding technique 472 00:13:45,610 --> 00:13:45,620 473 00:13:45,620 --> 00:13:48,740 we can view valve operation from 474 00:13:48,740 --> 00:13:48,750 we can view valve operation from 475 00:13:48,750 --> 00:13:52,340 we can view valve operation from different rotational views red particles 476 00:13:52,340 --> 00:13:52,350 different rotational views red particles 477 00:13:52,350 --> 00:13:53,810 different rotational views red particles are released from the vertical plane of 478 00:13:53,810 --> 00:13:53,820 are released from the vertical plane of 479 00:13:53,820 --> 00:13:56,510 are released from the vertical plane of the entrance and magenta particles are 480 00:13:56,510 --> 00:13:56,520 the entrance and magenta particles are 481 00:13:56,520 --> 00:13:58,250 the entrance and magenta particles are released from the sinus region of the 482 00:13:58,250 --> 00:13:58,260 released from the sinus region of the 483 00:13:58,260 --> 00:14:00,860 released from the sinus region of the aorta which is located just beyond the 484 00:14:00,860 --> 00:14:00,870 aorta which is located just beyond the 485 00:14:00,870 --> 00:14:04,640 aorta which is located just beyond the tilting disk the flow between the disk 486 00:14:04,640 --> 00:14:04,650 tilting disk the flow between the disk 487 00:14:04,650 --> 00:14:06,950 tilting disk the flow between the disk and the aortic wall is highly 488 00:14:06,950 --> 00:14:06,960 and the aortic wall is highly 489 00:14:06,960 --> 00:14:10,280 and the aortic wall is highly accelerated these kinds of changes in 490 00:14:10,280 --> 00:14:10,290 accelerated these kinds of changes in 491 00:14:10,290 --> 00:14:12,380 accelerated these kinds of changes in the local blood flow conditions can 492 00:14:12,380 --> 00:14:12,390 the local blood flow conditions can 493 00:14:12,390 --> 00:14:26,280 the local blood flow conditions can greatly affect the blood structure 494 00:14:26,280 --> 00:14:26,290 495 00:14:26,290 --> 00:14:28,510 technology developments that result from 496 00:14:28,510 --> 00:14:28,520 technology developments that result from 497 00:14:28,520 --> 00:14:30,970 technology developments that result from solving this problem will yield spin 498 00:14:30,970 --> 00:14:30,980 solving this problem will yield spin 499 00:14:30,980 --> 00:14:33,070 solving this problem will yield spin back applications for other flow 500 00:14:33,070 --> 00:14:33,080 back applications for other flow 501 00:14:33,080 --> 00:14:35,080 back applications for other flow problems associated with the space 502 00:14:35,080 --> 00:14:35,090 problems associated with the space 503 00:14:35,090 --> 00:14:38,110 problems associated with the space shuttle main engine an important 504 00:14:38,110 --> 00:14:38,120 shuttle main engine an important 505 00:14:38,120 --> 00:14:40,420 shuttle main engine an important contribution made by NASA to medicine 506 00:14:40,420 --> 00:14:40,430 contribution made by NASA to medicine 507 00:14:40,430 --> 00:14:42,610 contribution made by NASA to medicine results in a contribution made by 508 00:14:42,610 --> 00:14:42,620 results in a contribution made by 509 00:14:42,620 --> 00:14:46,180 results in a contribution made by medicine back to NASA science aiding 510 00:14:46,180 --> 00:14:46,190 medicine back to NASA science aiding 511 00:14:46,190 --> 00:14:47,650 medicine back to NASA science aiding science through interdisciplinary 512 00:14:47,650 --> 00:14:47,660 science through interdisciplinary 513 00:14:47,660 --> 00:15:05,759 science through interdisciplinary cooperation 514 00:15:05,759 --> 00:15:05,769 515 00:15:05,769 --> 00:15:09,430 the f-18 is a jet fighter currently used 516 00:15:09,430 --> 00:15:09,440 the f-18 is a jet fighter currently used 517 00:15:09,440 --> 00:15:12,340 the f-18 is a jet fighter currently used by the United States Navy it is used in 518 00:15:12,340 --> 00:15:12,350 by the United States Navy it is used in 519 00:15:12,350 --> 00:15:14,769 by the United States Navy it is used in air-to-air and air-to-ground fighter and 520 00:15:14,769 --> 00:15:14,779 air-to-air and air-to-ground fighter and 521 00:15:14,779 --> 00:15:17,590 air-to-air and air-to-ground fighter and attack roles by the fleet it has a great 522 00:15:17,590 --> 00:15:17,600 attack roles by the fleet it has a great 523 00:15:17,600 --> 00:15:19,900 attack roles by the fleet it has a great deal of maneuverability and performs at 524 00:15:19,900 --> 00:15:19,910 deal of maneuverability and performs at 525 00:15:19,910 --> 00:15:22,769 deal of maneuverability and performs at high G's and at high angles of attack 526 00:15:22,769 --> 00:15:22,779 high G's and at high angles of attack 527 00:15:22,779 --> 00:15:25,540 high G's and at high angles of attack Russell Cummings National Research 528 00:15:25,540 --> 00:15:25,550 Russell Cummings National Research 529 00:15:25,550 --> 00:15:27,970 Russell Cummings National Research Council research associate explains why 530 00:15:27,970 --> 00:15:27,980 Council research associate explains why 531 00:15:27,980 --> 00:15:30,280 Council research associate explains why the f-18 was chosen as a research 532 00:15:30,280 --> 00:15:30,290 the f-18 was chosen as a research 533 00:15:30,290 --> 00:15:33,939 the f-18 was chosen as a research vehicle the f-18 because it's capable of 534 00:15:33,939 --> 00:15:33,949 vehicle the f-18 because it's capable of 535 00:15:33,949 --> 00:15:36,249 vehicle the f-18 because it's capable of pulling such high manoeuvres and high 536 00:15:36,249 --> 00:15:36,259 pulling such high manoeuvres and high 537 00:15:36,259 --> 00:15:39,610 pulling such high manoeuvres and high G's gets into regimes of aerodynamics 538 00:15:39,610 --> 00:15:39,620 G's gets into regimes of aerodynamics 539 00:15:39,620 --> 00:15:40,960 G's gets into regimes of aerodynamics that other aircraft don't even 540 00:15:40,960 --> 00:15:40,970 that other aircraft don't even 541 00:15:40,970 --> 00:15:43,059 that other aircraft don't even experience because of that we're using 542 00:15:43,059 --> 00:15:43,069 experience because of that we're using 543 00:15:43,069 --> 00:15:46,600 experience because of that we're using it as a test bed and a computation basis 544 00:15:46,600 --> 00:15:46,610 it as a test bed and a computation basis 545 00:15:46,610 --> 00:15:50,199 it as a test bed and a computation basis for producing predictions for close over 546 00:15:50,199 --> 00:15:50,209 for producing predictions for close over 547 00:15:50,209 --> 00:15:55,030 for producing predictions for close over heinel attack aircraft the cfd process 548 00:15:55,030 --> 00:15:55,040 heinel attack aircraft the cfd process 549 00:15:55,040 --> 00:15:57,389 heinel attack aircraft the cfd process begins when the aircraft manufacturer 550 00:15:57,389 --> 00:15:57,399 begins when the aircraft manufacturer 551 00:15:57,399 --> 00:16:00,009 begins when the aircraft manufacturer supplies the surface geometry of the 552 00:16:00,009 --> 00:16:00,019 supplies the surface geometry of the 553 00:16:00,019 --> 00:16:02,590 supplies the surface geometry of the aircraft to be studied from this 554 00:16:02,590 --> 00:16:02,600 aircraft to be studied from this 555 00:16:02,600 --> 00:16:05,139 aircraft to be studied from this information a surface grid and a flow 556 00:16:05,139 --> 00:16:05,149 information a surface grid and a flow 557 00:16:05,149 --> 00:16:08,620 information a surface grid and a flow field grid is created then flow solving 558 00:16:08,620 --> 00:16:08,630 field grid is created then flow solving 559 00:16:08,630 --> 00:16:10,900 field grid is created then flow solving begins using the three-dimensional 560 00:16:10,900 --> 00:16:10,910 begins using the three-dimensional 561 00:16:10,910 --> 00:16:14,110 begins using the three-dimensional partially flux split time marching F 3d 562 00:16:14,110 --> 00:16:14,120 partially flux split time marching F 3d 563 00:16:14,120 --> 00:16:17,710 partially flux split time marching F 3d navier-stokes code predictions are made 564 00:16:17,710 --> 00:16:17,720 navier-stokes code predictions are made 565 00:16:17,720 --> 00:16:20,499 navier-stokes code predictions are made for turbulent flow by using the Baldwin 566 00:16:20,499 --> 00:16:20,509 for turbulent flow by using the Baldwin 567 00:16:20,509 --> 00:16:24,220 for turbulent flow by using the Baldwin Lomax turbulence model here we compare 568 00:16:24,220 --> 00:16:24,230 Lomax turbulence model here we compare 569 00:16:24,230 --> 00:16:27,370 Lomax turbulence model here we compare the flow visualization around the 1/32 570 00:16:27,370 --> 00:16:27,380 the flow visualization around the 1/32 571 00:16:27,380 --> 00:16:30,249 the flow visualization around the 1/32 scale model of the f-18 in the eidetic 572 00:16:30,249 --> 00:16:30,259 scale model of the f-18 in the eidetic 573 00:16:30,259 --> 00:16:32,439 scale model of the f-18 in the eidetic international water tunnel with the 574 00:16:32,439 --> 00:16:32,449 international water tunnel with the 575 00:16:32,449 --> 00:16:35,980 international water tunnel with the computational results clearly vortices 576 00:16:35,980 --> 00:16:35,990 computational results clearly vortices 577 00:16:35,990 --> 00:16:38,079 computational results clearly vortices from the fore body and wing leading-edge 578 00:16:38,079 --> 00:16:38,089 from the fore body and wing leading-edge 579 00:16:38,089 --> 00:17:04,550 from the fore body and wing leading-edge extension or Lex can be seen 580 00:17:04,550 --> 00:17:04,560 581 00:17:04,560 --> 00:17:06,500 we visualize our numerical predictions 582 00:17:06,500 --> 00:17:06,510 we visualize our numerical predictions 583 00:17:06,510 --> 00:17:09,790 we visualize our numerical predictions using a variety of methods including 584 00:17:09,790 --> 00:17:09,800 using a variety of methods including 585 00:17:09,800 --> 00:17:12,410 using a variety of methods including simulated surface oil flows which help 586 00:17:12,410 --> 00:17:12,420 simulated surface oil flows which help 587 00:17:12,420 --> 00:17:14,360 simulated surface oil flows which help us to see the primary and secondary 588 00:17:14,360 --> 00:17:14,370 us to see the primary and secondary 589 00:17:14,370 --> 00:17:16,730 us to see the primary and secondary cross flow separation lines on both the 590 00:17:16,730 --> 00:17:16,740 cross flow separation lines on both the 591 00:17:16,740 --> 00:17:18,800 cross flow separation lines on both the fuselage and the leading edge extension 592 00:17:18,800 --> 00:17:18,810 fuselage and the leading edge extension 593 00:17:18,810 --> 00:17:21,580 fuselage and the leading edge extension we also use felicity density contours 594 00:17:21,580 --> 00:17:21,590 we also use felicity density contours 595 00:17:21,590 --> 00:17:24,830 we also use felicity density contours which enable us to see both positive and 596 00:17:24,830 --> 00:17:24,840 which enable us to see both positive and 597 00:17:24,840 --> 00:17:27,190 which enable us to see both positive and negative senses of rotation of vortices 598 00:17:27,190 --> 00:17:27,200 negative senses of rotation of vortices 599 00:17:27,200 --> 00:17:30,380 negative senses of rotation of vortices we can further visualize vortices by 600 00:17:30,380 --> 00:17:30,390 we can further visualize vortices by 601 00:17:30,390 --> 00:17:32,720 we can further visualize vortices by passing particle traces back through the 602 00:17:32,720 --> 00:17:32,730 passing particle traces back through the 603 00:17:32,730 --> 00:17:35,270 passing particle traces back through the holistic on tours which help us see the 604 00:17:35,270 --> 00:17:35,280 holistic on tours which help us see the 605 00:17:35,280 --> 00:17:37,070 holistic on tours which help us see the vortices as they pass back over the 606 00:17:37,070 --> 00:17:37,080 vortices as they pass back over the 607 00:17:37,080 --> 00:17:40,790 vortices as they pass back over the fuselage the goal of the research is to 608 00:17:40,790 --> 00:17:40,800 fuselage the goal of the research is to 609 00:17:40,800 --> 00:17:42,680 fuselage the goal of the research is to be able to predict the flow over a full 610 00:17:42,680 --> 00:17:42,690 be able to predict the flow over a full 611 00:17:42,690 --> 00:17:45,980 be able to predict the flow over a full aircraft such as the f-18 so we can see 612 00:17:45,980 --> 00:17:45,990 aircraft such as the f-18 so we can see 613 00:17:45,990 --> 00:17:48,320 aircraft such as the f-18 so we can see the interaction of things such as the 614 00:17:48,320 --> 00:17:48,330 the interaction of things such as the 615 00:17:48,330 --> 00:17:50,870 the interaction of things such as the Lexx vortex as it comes up over on top 616 00:17:50,870 --> 00:17:50,880 Lexx vortex as it comes up over on top 617 00:17:50,880 --> 00:17:53,150 Lexx vortex as it comes up over on top of the Lex runs down the body and 618 00:17:53,150 --> 00:17:53,160 of the Lex runs down the body and 619 00:17:53,160 --> 00:17:54,680 of the Lex runs down the body and pinches on the vertical tail and 620 00:17:54,680 --> 00:17:54,690 pinches on the vertical tail and 621 00:17:54,690 --> 00:17:59,180 pinches on the vertical tail and possibly cause a structural damage in 622 00:17:59,180 --> 00:17:59,190 possibly cause a structural damage in 623 00:17:59,190 --> 00:18:01,370 possibly cause a structural damage in actual flight tests shown here on the 624 00:18:01,370 --> 00:18:01,380 actual flight tests shown here on the 625 00:18:01,380 --> 00:18:04,190 actual flight tests shown here on the fa-18 high alpha research vehicle or 626 00:18:04,190 --> 00:18:04,200 fa-18 high alpha research vehicle or 627 00:18:04,200 --> 00:18:07,490 fa-18 high alpha research vehicle or Harv note the effect of the Lex vortices 628 00:18:07,490 --> 00:18:07,500 Harv note the effect of the Lex vortices 629 00:18:07,500 --> 00:18:10,130 Harv note the effect of the Lex vortices on the vertical stabilizer as Russell 630 00:18:10,130 --> 00:18:10,140 on the vertical stabilizer as Russell 631 00:18:10,140 --> 00:18:12,740 on the vertical stabilizer as Russell Cummings continues there are flight 632 00:18:12,740 --> 00:18:12,750 Cummings continues there are flight 633 00:18:12,750 --> 00:18:14,720 Cummings continues there are flight tests being currently conducted done at 634 00:18:14,720 --> 00:18:14,730 tests being currently conducted done at 635 00:18:14,730 --> 00:18:17,720 tests being currently conducted done at Dryden and we're comparing our CFD 636 00:18:17,720 --> 00:18:17,730 Dryden and we're comparing our CFD 637 00:18:17,730 --> 00:18:20,180 Dryden and we're comparing our CFD predictions concurrently with them 638 00:18:20,180 --> 00:18:20,190 predictions concurrently with them 639 00:18:20,190 --> 00:18:22,700 predictions concurrently with them taking their data and it's very exciting 640 00:18:22,700 --> 00:18:22,710 taking their data and it's very exciting 641 00:18:22,710 --> 00:18:24,800 taking their data and it's very exciting since I don't believe that very many 642 00:18:24,800 --> 00:18:24,810 since I don't believe that very many 643 00:18:24,810 --> 00:18:25,910 since I don't believe that very many people have been able to do that before 644 00:18:25,910 --> 00:18:25,920 people have been able to do that before 645 00:18:25,920 --> 00:18:28,190 people have been able to do that before to actually have their CFD predictions 646 00:18:28,190 --> 00:18:28,200 to actually have their CFD predictions 647 00:18:28,200 --> 00:18:30,470 to actually have their CFD predictions hand in hand with flight test data and 648 00:18:30,470 --> 00:18:30,480 hand in hand with flight test data and 649 00:18:30,480 --> 00:18:32,780 hand in hand with flight test data and as we've compared the two side-by-side 650 00:18:32,780 --> 00:18:32,790 as we've compared the two side-by-side 651 00:18:32,790 --> 00:18:35,900 as we've compared the two side-by-side we've seen that the CFD has been able to 652 00:18:35,900 --> 00:18:35,910 we've seen that the CFD has been able to 653 00:18:35,910 --> 00:18:38,120 we've seen that the CFD has been able to very well predict the type of 654 00:18:38,120 --> 00:18:38,130 very well predict the type of 655 00:18:38,130 --> 00:18:40,130 very well predict the type of aerodynamics both for surface pressures 656 00:18:40,130 --> 00:18:40,140 aerodynamics both for surface pressures 657 00:18:40,140 --> 00:18:56,050 aerodynamics both for surface pressures and off surface flow visualizations 658 00:18:56,050 --> 00:18:56,060 659 00:18:56,060 --> 00:18:59,260 a multi-stage compressor is used on jet 660 00:18:59,260 --> 00:18:59,270 a multi-stage compressor is used on jet 661 00:18:59,270 --> 00:19:01,450 a multi-stage compressor is used on jet aircraft engines to compress the air 662 00:19:01,450 --> 00:19:01,460 aircraft engines to compress the air 663 00:19:01,460 --> 00:19:03,940 aircraft engines to compress the air before it goes into the combustion phase 664 00:19:03,940 --> 00:19:03,950 before it goes into the combustion phase 665 00:19:03,950 --> 00:19:07,030 before it goes into the combustion phase a multi-stage compressor consists of 666 00:19:07,030 --> 00:19:07,040 a multi-stage compressor consists of 667 00:19:07,040 --> 00:19:10,390 a multi-stage compressor consists of many rotor stator pairs rotors are 668 00:19:10,390 --> 00:19:10,400 many rotor stator pairs rotors are 669 00:19:10,400 --> 00:19:13,060 many rotor stator pairs rotors are rotating air foils and stators are 670 00:19:13,060 --> 00:19:13,070 rotating air foils and stators are 671 00:19:13,070 --> 00:19:15,970 rotating air foils and stators are stationary air foils in a multi-stage 672 00:19:15,970 --> 00:19:15,980 stationary air foils in a multi-stage 673 00:19:15,980 --> 00:19:17,800 stationary air foils in a multi-stage compressor you may have as many as 674 00:19:17,800 --> 00:19:17,810 compressor you may have as many as 675 00:19:17,810 --> 00:19:19,480 compressor you may have as many as seventeen to twenty of these rotor 676 00:19:19,480 --> 00:19:19,490 seventeen to twenty of these rotor 677 00:19:19,490 --> 00:19:21,600 seventeen to twenty of these rotor stator pairs 678 00:19:21,600 --> 00:19:21,610 stator pairs 679 00:19:21,610 --> 00:19:24,940 stator pairs Karen Gundy Berlet research scientists 680 00:19:24,940 --> 00:19:24,950 Karen Gundy Berlet research scientists 681 00:19:24,950 --> 00:19:27,400 Karen Gundy Berlet research scientists at Ames Research Center explains the 682 00:19:27,400 --> 00:19:27,410 at Ames Research Center explains the 683 00:19:27,410 --> 00:19:29,380 at Ames Research Center explains the difficulty of doing research in this 684 00:19:29,380 --> 00:19:29,390 difficulty of doing research in this 685 00:19:29,390 --> 00:19:29,830 difficulty of doing research in this arena 686 00:19:29,830 --> 00:19:29,840 arena 687 00:19:29,840 --> 00:19:33,310 arena the goals of my project are to compute 688 00:19:33,310 --> 00:19:33,320 the goals of my project are to compute 689 00:19:33,320 --> 00:19:35,710 the goals of my project are to compute the three-dimensional flow within a 690 00:19:35,710 --> 00:19:35,720 the three-dimensional flow within a 691 00:19:35,720 --> 00:19:38,530 the three-dimensional flow within a multi-stage compressor and hopefully by 692 00:19:38,530 --> 00:19:38,540 multi-stage compressor and hopefully by 693 00:19:38,540 --> 00:19:40,810 multi-stage compressor and hopefully by doing this we can understand the fluid 694 00:19:40,810 --> 00:19:40,820 doing this we can understand the fluid 695 00:19:40,820 --> 00:19:42,010 doing this we can understand the fluid physics of the flow within the 696 00:19:42,010 --> 00:19:42,020 physics of the flow within the 697 00:19:42,020 --> 00:19:43,990 physics of the flow within the compressor see if we can design 698 00:19:43,990 --> 00:19:44,000 compressor see if we can design 699 00:19:44,000 --> 00:19:46,690 compressor see if we can design compressors that are much more efficient 700 00:19:46,690 --> 00:19:46,700 compressors that are much more efficient 701 00:19:46,700 --> 00:19:49,810 compressors that are much more efficient and much more reliable while reducing 702 00:19:49,810 --> 00:19:49,820 and much more reliable while reducing 703 00:19:49,820 --> 00:19:51,310 and much more reliable while reducing the weight and the size of the 704 00:19:51,310 --> 00:19:51,320 the weight and the size of the 705 00:19:51,320 --> 00:19:55,450 the weight and the size of the compressor here we see the results of 706 00:19:55,450 --> 00:19:55,460 compressor here we see the results of 707 00:19:55,460 --> 00:19:58,090 compressor here we see the results of this research these are the pressure 708 00:19:58,090 --> 00:19:58,100 this research these are the pressure 709 00:19:58,100 --> 00:20:00,460 this research these are the pressure contours within the aircraft engine 710 00:20:00,460 --> 00:20:00,470 contours within the aircraft engine 711 00:20:00,470 --> 00:20:02,560 contours within the aircraft engine compressor the flow is moving from left 712 00:20:02,560 --> 00:20:02,570 compressor the flow is moving from left 713 00:20:02,570 --> 00:20:05,860 compressor the flow is moving from left to right low pressure is indicated by 714 00:20:05,860 --> 00:20:05,870 to right low pressure is indicated by 715 00:20:05,870 --> 00:20:08,410 to right low pressure is indicated by blue whereas high pressure is indicated 716 00:20:08,410 --> 00:20:08,420 blue whereas high pressure is indicated 717 00:20:08,420 --> 00:20:11,500 blue whereas high pressure is indicated by red the pressure contours show the 718 00:20:11,500 --> 00:20:11,510 by red the pressure contours show the 719 00:20:11,510 --> 00:20:13,900 by red the pressure contours show the inviscid part of the flow field by 720 00:20:13,900 --> 00:20:13,910 inviscid part of the flow field by 721 00:20:13,910 --> 00:20:15,400 inviscid part of the flow field by seeing the pressure difference across 722 00:20:15,400 --> 00:20:15,410 seeing the pressure difference across 723 00:20:15,410 --> 00:20:18,160 seeing the pressure difference across each of the air foils you can see what 724 00:20:18,160 --> 00:20:18,170 each of the air foils you can see what 725 00:20:18,170 --> 00:20:20,790 each of the air foils you can see what forces are occurring on the airfoil 726 00:20:20,790 --> 00:20:20,800 forces are occurring on the airfoil 727 00:20:20,800 --> 00:20:22,930 forces are occurring on the airfoil notice that the pressure within the 728 00:20:22,930 --> 00:20:22,940 notice that the pressure within the 729 00:20:22,940 --> 00:20:25,720 notice that the pressure within the system is quite unsteady as the pressure 730 00:20:25,720 --> 00:20:25,730 system is quite unsteady as the pressure 731 00:20:25,730 --> 00:20:28,150 system is quite unsteady as the pressure rises from the first stage to the second 732 00:20:28,150 --> 00:20:28,160 rises from the first stage to the second 733 00:20:28,160 --> 00:20:29,610 rises from the first stage to the second stage 734 00:20:29,610 --> 00:20:29,620 stage 735 00:20:29,620 --> 00:20:32,440 stage these are the entropy contours within 736 00:20:32,440 --> 00:20:32,450 these are the entropy contours within 737 00:20:32,450 --> 00:20:35,110 these are the entropy contours within the two-and-a-half stage compressor the 738 00:20:35,110 --> 00:20:35,120 the two-and-a-half stage compressor the 739 00:20:35,120 --> 00:20:37,390 the two-and-a-half stage compressor the entropy shows that viscous part of the 740 00:20:37,390 --> 00:20:37,400 entropy shows that viscous part of the 741 00:20:37,400 --> 00:20:40,900 entropy shows that viscous part of the flow field it points out the slow fluid 742 00:20:40,900 --> 00:20:40,910 flow field it points out the slow fluid 743 00:20:40,910 --> 00:20:42,640 flow field it points out the slow fluid that sticks to the surface of the air 744 00:20:42,640 --> 00:20:42,650 that sticks to the surface of the air 745 00:20:42,650 --> 00:20:43,530 that sticks to the surface of the air force 746 00:20:43,530 --> 00:20:43,540 force 747 00:20:43,540 --> 00:20:46,299 force notice that the slow fluid is convected 748 00:20:46,299 --> 00:20:46,309 notice that the slow fluid is convected 749 00:20:46,309 --> 00:20:48,520 notice that the slow fluid is convected back through the system for three or 750 00:20:48,520 --> 00:20:48,530 back through the system for three or 751 00:20:48,530 --> 00:20:51,340 back through the system for three or four cord lengths in a multi-stage 752 00:20:51,340 --> 00:20:51,350 four cord lengths in a multi-stage 753 00:20:51,350 --> 00:20:53,470 four cord lengths in a multi-stage compressor the flow within the latter 754 00:20:53,470 --> 00:20:53,480 compressor the flow within the latter 755 00:20:53,480 --> 00:20:56,080 compressor the flow within the latter stages is much more complex than the 756 00:20:56,080 --> 00:20:56,090 stages is much more complex than the 757 00:20:56,090 --> 00:20:58,570 stages is much more complex than the flow for the initial stages easily seen 758 00:20:58,570 --> 00:20:58,580 flow for the initial stages easily seen 759 00:20:58,580 --> 00:21:02,250 flow for the initial stages easily seen here the entropy plot does a good job 760 00:21:02,250 --> 00:21:02,260 here the entropy plot does a good job 761 00:21:02,260 --> 00:21:04,750 here the entropy plot does a good job showing the wakes due to the viscous 762 00:21:04,750 --> 00:21:04,760 showing the wakes due to the viscous 763 00:21:04,760 --> 00:21:06,850 showing the wakes due to the viscous dissipation of the air next to the air 764 00:21:06,850 --> 00:21:06,860 dissipation of the air next to the air 765 00:21:06,860 --> 00:21:09,790 dissipation of the air next to the air fourth as the wakes progress along the 766 00:21:09,790 --> 00:21:09,800 fourth as the wakes progress along the 767 00:21:09,800 --> 00:21:12,400 fourth as the wakes progress along the surfaces of the airfoils note that there 768 00:21:12,400 --> 00:21:12,410 surfaces of the airfoils note that there 769 00:21:12,410 --> 00:21:15,040 surfaces of the airfoils note that there are varying forces applied that tend to 770 00:21:15,040 --> 00:21:15,050 are varying forces applied that tend to 771 00:21:15,050 --> 00:21:18,130 are varying forces applied that tend to twist and rotate the air ports in the 772 00:21:18,130 --> 00:21:18,140 twist and rotate the air ports in the 773 00:21:18,140 --> 00:21:20,290 twist and rotate the air ports in the latter stages where there are many wakes 774 00:21:20,290 --> 00:21:20,300 latter stages where there are many wakes 775 00:21:20,300 --> 00:21:21,940 latter stages where there are many wakes being conducted through the compressor 776 00:21:21,940 --> 00:21:21,950 being conducted through the compressor 777 00:21:21,950 --> 00:21:25,900 being conducted through the compressor the forces are even more severe the flow 778 00:21:25,900 --> 00:21:25,910 the forces are even more severe the flow 779 00:21:25,910 --> 00:21:28,030 the forces are even more severe the flow fields are very complicated and the 780 00:21:28,030 --> 00:21:28,040 fields are very complicated and the 781 00:21:28,040 --> 00:21:30,549 fields are very complicated and the unsteady forces appear to be varying 782 00:21:30,549 --> 00:21:30,559 unsteady forces appear to be varying 783 00:21:30,559 --> 00:21:33,940 unsteady forces appear to be varying quite rapidly there are is experimental 784 00:21:33,940 --> 00:21:33,950 quite rapidly there are is experimental 785 00:21:33,950 --> 00:21:35,860 quite rapidly there are is experimental data available for this compressor 786 00:21:35,860 --> 00:21:35,870 data available for this compressor 787 00:21:35,870 --> 00:21:37,630 data available for this compressor that's why we chose to can simulate the 788 00:21:37,630 --> 00:21:37,640 that's why we chose to can simulate the 789 00:21:37,640 --> 00:21:40,120 that's why we chose to can simulate the flow within this compressor so far the 790 00:21:40,120 --> 00:21:40,130 flow within this compressor so far the 791 00:21:40,130 --> 00:21:42,490 flow within this compressor so far the comparisons have been very good time 792 00:21:42,490 --> 00:21:42,500 comparisons have been very good time 793 00:21:42,500 --> 00:21:44,140 comparisons have been very good time average pressures on the surface are 794 00:21:44,140 --> 00:21:44,150 average pressures on the surface are 795 00:21:44,150 --> 00:21:46,020 average pressures on the surface are very close to the experimental values 796 00:21:46,020 --> 00:21:46,030 very close to the experimental values 797 00:21:46,030 --> 00:21:48,970 very close to the experimental values awake average data is in good comparison 798 00:21:48,970 --> 00:21:48,980 awake average data is in good comparison 799 00:21:48,980 --> 00:21:51,730 awake average data is in good comparison for computations where I have an 800 00:21:51,730 --> 00:21:51,740 for computations where I have an 801 00:21:51,740 --> 00:21:53,590 for computations where I have an extremely fine grid in the second stage 802 00:21:53,590 --> 00:21:53,600 extremely fine grid in the second stage 803 00:21:53,600 --> 00:21:57,549 extremely fine grid in the second stage of the compressor one of the directions 804 00:21:57,549 --> 00:21:57,559 of the compressor one of the directions 805 00:21:57,559 --> 00:21:59,500 of the compressor one of the directions I see for computational fluid dynamics 806 00:21:59,500 --> 00:21:59,510 I see for computational fluid dynamics 807 00:21:59,510 --> 00:22:01,320 I see for computational fluid dynamics in the future is in an area we call 808 00:22:01,320 --> 00:22:01,330 in the future is in an area we call 809 00:22:01,330 --> 00:22:04,510 in the future is in an area we call multidisciplinary physics in that area 810 00:22:04,510 --> 00:22:04,520 multidisciplinary physics in that area 811 00:22:04,520 --> 00:22:07,030 multidisciplinary physics in that area we combined not only the fluid equations 812 00:22:07,030 --> 00:22:07,040 we combined not only the fluid equations 813 00:22:07,040 --> 00:22:08,970 we combined not only the fluid equations but the equations governing 814 00:22:08,970 --> 00:22:08,980 but the equations governing 815 00:22:08,980 --> 00:22:11,169 but the equations governing electromagnetics or propulsions or 816 00:22:11,169 --> 00:22:11,179 electromagnetics or propulsions or 817 00:22:11,179 --> 00:22:14,020 electromagnetics or propulsions or controls into one software simulation 818 00:22:14,020 --> 00:22:14,030 controls into one software simulation 819 00:22:14,030 --> 00:22:16,900 controls into one software simulation tool in order to solve problems like 820 00:22:16,900 --> 00:22:16,910 tool in order to solve problems like 821 00:22:16,910 --> 00:22:18,210 tool in order to solve problems like that the problems of multidisciplinary 822 00:22:18,210 --> 00:22:18,220 that the problems of multidisciplinary 823 00:22:18,220 --> 00:22:20,680 that the problems of multidisciplinary fluid physics it's going to require 824 00:22:20,680 --> 00:22:20,690 fluid physics it's going to require 825 00:22:20,690 --> 00:22:22,750 fluid physics it's going to require computers a thousand times faster than 826 00:22:22,750 --> 00:22:22,760 computers a thousand times faster than 827 00:22:22,760 --> 00:22:25,000 computers a thousand times faster than the computers we have today computers on 828 00:22:25,000 --> 00:22:25,010 the computers we have today computers on 829 00:22:25,010 --> 00:22:27,310 the computers we have today computers on the speed of 1 teraflop that's one 830 00:22:27,310 --> 00:22:27,320 the speed of 1 teraflop that's one 831 00:22:27,320 --> 00:22:29,290 the speed of 1 teraflop that's one trillion floating-point operations per 832 00:22:29,290 --> 00:22:29,300 trillion floating-point operations per 833 00:22:29,300 --> 00:22:32,049 trillion floating-point operations per second in order to obtain the 1 teraflop 834 00:22:32,049 --> 00:22:32,059 second in order to obtain the 1 teraflop 835 00:22:32,059 --> 00:22:33,850 second in order to obtain the 1 teraflop capability that we'll need for 836 00:22:33,850 --> 00:22:33,860 capability that we'll need for 837 00:22:33,860 --> 00:22:36,520 capability that we'll need for performing multidisciplinary simulations 838 00:22:36,520 --> 00:22:36,530 performing multidisciplinary simulations 839 00:22:36,530 --> 00:22:39,130 performing multidisciplinary simulations it's going to require massively parallel 840 00:22:39,130 --> 00:22:39,140 it's going to require massively parallel 841 00:22:39,140 --> 00:22:42,010 it's going to require massively parallel computers computers that have thousands 842 00:22:42,010 --> 00:22:42,020 computers computers that have thousands 843 00:22:42,020 --> 00:22:42,520 computers computers that have thousands and thousands 844 00:22:42,520 --> 00:22:42,530 and thousands 845 00:22:42,530 --> 00:22:46,180 and thousands of processors as compared to the ymp 846 00:22:46,180 --> 00:22:46,190 of processors as compared to the ymp 847 00:22:46,190 --> 00:22:48,970 of processors as compared to the ymp which has eight processors the 848 00:22:48,970 --> 00:22:48,980 which has eight processors the 849 00:22:48,980 --> 00:22:50,410 which has eight processors the internationalization of the aerospace 850 00:22:50,410 --> 00:22:50,420 internationalization of the aerospace 851 00:22:50,420 --> 00:22:52,930 internationalization of the aerospace business is going to cause CFD to play 852 00:22:52,930 --> 00:22:52,940 business is going to cause CFD to play 853 00:22:52,940 --> 00:22:55,150 business is going to cause CFD to play an even greater role in the simulation 854 00:22:55,150 --> 00:22:55,160 an even greater role in the simulation 855 00:22:55,160 --> 00:22:57,820 an even greater role in the simulation sciences area our American aerospace 856 00:22:57,820 --> 00:22:57,830 sciences area our American aerospace 857 00:22:57,830 --> 00:22:59,770 sciences area our American aerospace manufacturers are going to rely have 858 00:22:59,770 --> 00:22:59,780 manufacturers are going to rely have 859 00:22:59,780 --> 00:23:01,600 manufacturers are going to rely have more heavily on computational fluid 860 00:23:01,600 --> 00:23:01,610 more heavily on computational fluid 861 00:23:01,610 --> 00:23:03,670 more heavily on computational fluid dynamics to produce better and more 862 00:23:03,670 --> 00:23:03,680 dynamics to produce better and more 863 00:23:03,680 --> 00:23:05,230 dynamics to produce better and more efficient aircraft in order to be 864 00:23:05,230 --> 00:23:05,240 efficient aircraft in order to be 865 00:23:05,240 --> 00:23:07,000 efficient aircraft in order to be competitive with our overseas 866 00:23:07,000 --> 00:23:07,010 competitive with our overseas 867 00:23:07,010 --> 00:24:20,380 competitive with our overseas competitors 868 00:24:20,380 --> 00:24:20,390 869 00:24:20,390 --> 00:24:22,450 you