PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 100,000 Max Cl/Cd: 63.95 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu94097-il-100000.txt Download as CSV file: xf-psu94097-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3216 0.09598 0.09156 -0.0364 1.0000 0.0774
-7.500 -0.3358 0.09497 0.09067 -0.0336 1.0000 0.0788
-7.250 -0.3574 0.09467 0.09050 -0.0294 1.0000 0.0793
-7.000 -0.3806 0.09445 0.09039 -0.0251 1.0000 0.0796
-6.750 -0.3991 0.09359 0.08962 -0.0228 1.0000 0.0806
-6.500 -0.4143 0.09222 0.08834 -0.0228 1.0000 0.0819
-6.250 -0.4263 0.09021 0.08640 -0.0281 1.0000 0.0832
-6.000 -0.4171 0.08495 0.08114 -0.0348 0.9974 0.0849
-5.750 -0.4011 0.08186 0.07806 -0.0304 0.9946 0.0886
-5.500 -0.3602 0.07446 0.07038 -0.0520 0.9861 0.0985
-5.250 -0.3435 0.07112 0.06718 -0.0482 0.9833 0.1019
-5.000 -0.3097 0.06535 0.06116 -0.0603 0.9760 0.1133
-4.750 -0.2790 0.06175 0.05749 -0.0642 0.9715 0.1244
-4.500 -0.2539 0.05763 0.05335 -0.0671 0.9668 0.1318
-4.250 -0.2231 0.05374 0.04931 -0.0721 0.9609 0.1462
-4.000 -0.1815 0.04960 0.04489 -0.0795 0.9569 0.1710
-3.750 -0.0989 0.03645 0.03009 -0.0928 0.9559 0.0664
-3.500 -0.0583 0.03212 0.02487 -0.0953 0.9514 0.0540
-3.250 -0.0169 0.02912 0.02130 -0.0979 0.9476 0.0513
-3.000 0.0270 0.02727 0.01890 -0.1007 0.9442 0.0552
-2.750 0.0731 0.02510 0.01641 -0.1038 0.9419 0.0594
-2.500 0.1035 0.02407 0.01529 -0.1043 0.9360 0.0694
-2.250 0.1443 0.02255 0.01395 -0.1069 0.9321 0.1104
-2.000 0.1906 0.01948 0.01314 -0.1112 0.9308 0.5719
-1.750 0.2050 0.01896 0.01332 -0.1063 0.9259 0.8403
-1.500 0.2260 0.01893 0.01315 -0.1045 0.9175 1.0000
-1.250 0.2711 0.01910 0.01290 -0.1082 0.9136 1.0000
-1.000 0.2956 0.01951 0.01305 -0.1082 0.9051 1.0000
-0.750 0.3379 0.01968 0.01295 -0.1112 0.9006 1.0000
-0.500 0.3637 0.02010 0.01318 -0.1114 0.8924 1.0000
-0.250 0.4036 0.02026 0.01314 -0.1138 0.8873 1.0000
0.000 0.4310 0.02065 0.01339 -0.1142 0.8794 1.0000
0.250 0.4676 0.02080 0.01340 -0.1159 0.8735 1.0000
0.500 0.4947 0.02118 0.01367 -0.1160 0.8653 1.0000
0.750 0.5309 0.02125 0.01365 -0.1174 0.8592 1.0000
1.000 0.5567 0.02164 0.01398 -0.1173 0.8503 1.0000
1.250 0.5935 0.02159 0.01386 -0.1185 0.8445 1.0000
1.500 0.6180 0.02196 0.01420 -0.1181 0.8346 1.0000
1.750 0.6565 0.02167 0.01387 -0.1191 0.8294 1.0000
2.000 0.6802 0.02199 0.01418 -0.1184 0.8183 1.0000
2.250 0.7078 0.02211 0.01431 -0.1180 0.8088 1.0000
2.500 0.7424 0.02177 0.01396 -0.1182 0.8021 1.0000
2.750 0.7673 0.02196 0.01417 -0.1175 0.7910 1.0000
3.000 0.7953 0.02192 0.01414 -0.1169 0.7813 1.0000
3.250 0.8283 0.02146 0.01373 -0.1166 0.7737 1.0000
3.500 0.8539 0.02148 0.01380 -0.1157 0.7619 1.0000
3.750 0.8808 0.02138 0.01375 -0.1148 0.7506 1.0000
4.000 0.9095 0.02111 0.01353 -0.1140 0.7400 1.0000
4.250 0.9410 0.02057 0.01304 -0.1133 0.7307 1.0000
4.500 0.9676 0.02039 0.01293 -0.1123 0.7176 1.0000
4.750 0.9945 0.02014 0.01276 -0.1113 0.7039 1.0000
5.000 1.0220 0.01983 0.01255 -0.1102 0.6896 1.0000
5.250 1.0498 0.01947 0.01225 -0.1092 0.6744 1.0000
5.500 1.0738 0.01936 0.01225 -0.1079 0.6547 1.0000
5.750 1.1006 0.01901 0.01197 -0.1067 0.6350 1.0000
6.000 1.1253 0.01879 0.01186 -0.1054 0.6113 1.0000
6.250 1.1499 0.01860 0.01172 -0.1040 0.5838 1.0000
6.500 1.1736 0.01852 0.01163 -0.1025 0.5514 1.0000
6.750 1.1953 0.01869 0.01174 -0.1008 0.5130 1.0000
7.000 1.2154 0.01912 0.01203 -0.0991 0.4708 1.0000
7.250 1.2338 0.01983 0.01258 -0.0972 0.4283 1.0000
7.500 1.2509 0.02074 0.01330 -0.0954 0.3881 1.0000
7.750 1.2671 0.02179 0.01413 -0.0936 0.3522 1.0000
8.000 1.2826 0.02287 0.01513 -0.0918 0.3182 1.0000
8.250 1.2971 0.02401 0.01617 -0.0899 0.2874 1.0000
8.500 1.3107 0.02520 0.01727 -0.0879 0.2587 1.0000
8.750 1.3226 0.02643 0.01844 -0.0858 0.2314 1.0000
9.000 1.3329 0.02773 0.01974 -0.0835 0.2052 1.0000
9.250 1.3411 0.02915 0.02111 -0.0810 0.1804 1.0000
9.500 1.3466 0.03070 0.02253 -0.0782 0.1574 1.0000
9.750 1.3490 0.03225 0.02412 -0.0749 0.1360 1.0000
10.000 1.3513 0.03415 0.02589 -0.0720 0.1175 1.0000
10.250 1.3553 0.03618 0.02797 -0.0693 0.1006 1.0000
10.500 1.3599 0.03834 0.03013 -0.0668 0.0869 1.0000
10.750 1.3656 0.04062 0.03244 -0.0646 0.0756 1.0000
11.000 1.3748 0.04315 0.03496 -0.0626 0.0662 1.0000
11.250 1.3849 0.04587 0.03757 -0.0610 0.0571 1.0000
11.500 1.3864 0.04824 0.04035 -0.0585 0.0517 1.0000
11.750 1.3948 0.05144 0.04357 -0.0570 0.0453 1.0000
12.000 1.3951 0.05447 0.04702 -0.0547 0.0416 1.0000
12.250 1.3935 0.05712 0.04974 -0.0530 0.0378 1.0000
12.500 1.3920 0.06152 0.05437 -0.0512 0.0349 1.0000
12.750 1.3830 0.06551 0.05878 -0.0494 0.0339 1.0000
13.000 1.3716 0.06982 0.06346 -0.0480 0.0330 1.0000
13.250 1.3571 0.07436 0.06832 -0.0471 0.0322 1.0000
13.500 1.3413 0.07916 0.07342 -0.0468 0.0315 1.0000
13.750 1.3236 0.08443 0.07898 -0.0472 0.0313 1.0000
14.000 1.3041 0.09016 0.08497 -0.0483 0.0311 1.0000
14.250 1.2815 0.09673 0.09182 -0.0503 0.0315 1.0000
14.500 1.2577 0.10401 0.09936 -0.0533 0.0322 1.0000
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Polar data table (+)
Polar graphs
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