PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 200,000 Max Cl/Cd: 90.79 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu94097-il-200000.txt Download as CSV file: xf-psu94097-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: PSU 94-097 (AIAA 2001-2478)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3159 0.09655 0.09330 -0.0406 1.0000 0.0320
-8.000 -0.3278 0.09525 0.09210 -0.0395 1.0000 0.0323
-7.750 -0.3540 0.09560 0.09257 -0.0334 1.0000 0.0322
-7.500 -0.3379 0.09107 0.08806 -0.0430 0.9925 0.0326
-7.250 -0.3085 0.08482 0.08178 -0.0556 0.9853 0.0328
-7.000 -0.2974 0.07792 0.07492 -0.0587 0.9818 0.0340
-6.750 -0.2786 0.07464 0.07161 -0.0599 0.9767 0.0354
-6.500 -0.2507 0.06989 0.06683 -0.0674 0.9722 0.0374
-6.250 -0.2198 0.06405 0.06093 -0.0780 0.9660 0.0400
-6.000 -0.1685 0.05573 0.05209 -0.0984 0.9574 0.0443
-5.750 -0.1519 0.04896 0.04533 -0.1023 0.9510 0.0460
-5.500 -0.1279 0.04626 0.04264 -0.1040 0.9453 0.0486
-5.000 -0.0713 0.03842 0.03432 -0.1118 0.9319 0.0617
-4.750 -0.0405 0.03508 0.03063 -0.1150 0.9271 0.0736
-4.250 0.0294 0.02436 0.01815 -0.1170 0.9147 0.0334
-4.000 0.0572 0.02118 0.01468 -0.1173 0.9082 0.0300
-3.750 0.0871 0.01897 0.01205 -0.1173 0.9026 0.0283
-3.500 0.1164 0.01741 0.01021 -0.1170 0.8976 0.0281
-3.250 0.1442 0.01627 0.00894 -0.1167 0.8909 0.0293
-3.000 0.1730 0.01533 0.00788 -0.1164 0.8862 0.0323
-2.750 0.2014 0.01437 0.00691 -0.1166 0.8797 0.0460
-2.500 0.2317 0.01285 0.00600 -0.1175 0.8744 0.1778
-2.250 0.2601 0.01189 0.00583 -0.1182 0.8698 0.4048
-2.000 0.2850 0.01127 0.00595 -0.1177 0.8632 0.6271
-1.750 0.3068 0.01099 0.00594 -0.1156 0.8584 0.7506
-1.500 0.3246 0.01087 0.00597 -0.1127 0.8518 0.8356
-1.250 0.3402 0.01068 0.00582 -0.1091 0.8460 0.9183
-1.000 0.3729 0.01057 0.00557 -0.1098 0.8410 1.0000
-0.750 0.4024 0.01067 0.00551 -0.1104 0.8345 1.0000
-0.500 0.4319 0.01071 0.00537 -0.1106 0.8298 1.0000
-0.250 0.4607 0.01085 0.00540 -0.1110 0.8229 1.0000
0.000 0.4896 0.01089 0.00532 -0.1111 0.8173 1.0000
0.250 0.5180 0.01100 0.00533 -0.1113 0.8108 1.0000
0.500 0.5465 0.01107 0.00530 -0.1114 0.8043 1.0000
0.750 0.5749 0.01115 0.00530 -0.1114 0.7981 1.0000
1.000 0.6030 0.01121 0.00529 -0.1114 0.7905 1.0000
1.250 0.6311 0.01126 0.00527 -0.1112 0.7832 1.0000
1.500 0.6591 0.01130 0.00524 -0.1111 0.7754 1.0000
1.750 0.6870 0.01138 0.00529 -0.1111 0.7675 1.0000
2.000 0.7152 0.01140 0.00526 -0.1109 0.7602 1.0000
2.250 0.7427 0.01148 0.00533 -0.1108 0.7512 1.0000
2.500 0.7710 0.01149 0.00527 -0.1106 0.7440 1.0000
2.750 0.7984 0.01156 0.00535 -0.1105 0.7341 1.0000
3.000 0.8261 0.01162 0.00543 -0.1103 0.7249 1.0000
3.250 0.8542 0.01163 0.00539 -0.1101 0.7166 1.0000
3.500 0.8814 0.01169 0.00549 -0.1099 0.7055 1.0000
3.750 0.9086 0.01174 0.00556 -0.1097 0.6946 1.0000
4.000 0.9360 0.01178 0.00563 -0.1095 0.6835 1.0000
4.250 0.9632 0.01181 0.00568 -0.1092 0.6715 1.0000
4.500 0.9902 0.01185 0.00574 -0.1089 0.6582 1.0000
4.750 1.0168 0.01190 0.00583 -0.1085 0.6430 1.0000
5.000 1.0431 0.01196 0.00595 -0.1081 0.6254 1.0000
5.250 1.0692 0.01203 0.00602 -0.1076 0.6060 1.0000
5.500 1.0947 0.01215 0.00616 -0.1071 0.5823 1.0000
5.750 1.1195 0.01233 0.00632 -0.1064 0.5544 1.0000
6.000 1.1432 0.01263 0.00655 -0.1055 0.5213 1.0000
6.250 1.1657 0.01306 0.00687 -0.1046 0.4819 1.0000
6.500 1.1865 0.01365 0.00729 -0.1034 0.4383 1.0000
6.750 1.2060 0.01439 0.00783 -0.1022 0.3951 1.0000
7.000 1.2250 0.01519 0.00845 -0.1009 0.3548 1.0000
7.250 1.2436 0.01600 0.00916 -0.0997 0.3191 1.0000
7.500 1.2620 0.01684 0.00988 -0.0984 0.2874 1.0000
7.750 1.2798 0.01768 0.01064 -0.0971 0.2584 1.0000
8.000 1.2974 0.01852 0.01141 -0.0958 0.2317 1.0000
8.250 1.3143 0.01939 0.01222 -0.0944 0.2065 1.0000
8.500 1.3301 0.02030 0.01306 -0.0928 0.1820 1.0000
8.750 1.3443 0.02129 0.01401 -0.0911 0.1588 1.0000
9.000 1.3585 0.02226 0.01496 -0.0893 0.1355 1.0000
9.250 1.3694 0.02340 0.01605 -0.0872 0.1136 1.0000
9.500 1.3749 0.02476 0.01730 -0.0842 0.0940 1.0000
9.750 1.3811 0.02623 0.01875 -0.0815 0.0758 1.0000
10.000 1.3849 0.02795 0.02045 -0.0787 0.0624 1.0000
10.250 1.3882 0.02979 0.02230 -0.0761 0.0523 1.0000
10.500 1.3887 0.03193 0.02444 -0.0735 0.0450 1.0000
10.750 1.3946 0.03367 0.02627 -0.0716 0.0383 1.0000
11.000 1.3946 0.03607 0.02877 -0.0692 0.0335 1.0000
11.250 1.3972 0.03820 0.03098 -0.0675 0.0281 1.0000
11.500 1.3972 0.04076 0.03369 -0.0655 0.0239 1.0000
11.750 1.3965 0.04332 0.03628 -0.0641 0.0198 1.0000
12.000 1.3929 0.04648 0.03962 -0.0620 0.0172 1.0000
12.250 1.3935 0.04912 0.04239 -0.0608 0.0149 1.0000
12.500 1.3874 0.05256 0.04588 -0.0595 0.0133 1.0000
12.750 1.3852 0.05574 0.04926 -0.0583 0.0119 1.0000
13.000 1.3853 0.05860 0.05230 -0.0578 0.0106 1.0000
13.250 1.3828 0.06179 0.05561 -0.0575 0.0097 1.0000
13.500 1.3771 0.06549 0.05942 -0.0571 0.0091 1.0000
13.750 1.3683 0.06979 0.06385 -0.0563 0.0087 1.0000
14.000 1.3577 0.07458 0.06886 -0.0556 0.0084 1.0000
14.250 1.3506 0.07901 0.07352 -0.0560 0.0082 1.0000
14.500 1.3417 0.08387 0.07863 -0.0567 0.0081 1.0000
14.750 1.3311 0.08920 0.08420 -0.0579 0.0080 1.0000
15.000 1.3191 0.09495 0.09018 -0.0596 0.0079 1.0000
15.250 1.3058 0.10122 0.09669 -0.0619 0.0078 1.0000
15.500 1.2917 0.10797 0.10366 -0.0648 0.0078 1.0000
15.750 1.2773 0.11509 0.11099 -0.0683 0.0078 1.0000
16.000 1.2621 0.12272 0.11883 -0.0724 0.0078 1.0000
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Polar data table (+)
Polar graphs
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