GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 100,000 Max Cl/Cd: 46.38 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe503-il-100000-n5.txt Download as CSV file: xf-goe503-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0741 0.09910 0.09427 -0.0947 0.9315 0.0343
-10.250 -0.0729 0.09389 0.08909 -0.0979 0.9228 0.0346
-10.000 -0.0699 0.08778 0.08298 -0.1028 0.9172 0.0350
-9.750 -0.0776 0.08156 0.07679 -0.1066 0.9064 0.0358
-9.500 -0.0540 0.08033 0.07552 -0.1089 0.8993 0.0375
-9.250 -0.0507 0.07558 0.07077 -0.1129 0.8896 0.0390
-9.000 -0.0631 0.06925 0.06447 -0.1175 0.8771 0.0400
-8.750 -0.0955 0.06169 0.05691 -0.1217 0.8617 0.0403
-8.500 -0.1874 0.04378 0.03851 -0.1260 0.8429 0.0396
-8.250 -0.2138 0.03669 0.03067 -0.1237 0.8304 0.0410
-8.000 -0.1968 0.03391 0.02750 -0.1239 0.8247 0.0438
-7.750 -0.1859 0.03272 0.02613 -0.1218 0.8144 0.0467
-7.500 -0.1651 0.03028 0.02318 -0.1218 0.8090 0.0519
-7.250 -0.1483 0.02992 0.02276 -0.1201 0.7994 0.0561
-7.000 -0.1223 0.02842 0.02088 -0.1204 0.7938 0.0624
-6.750 -0.1025 0.02815 0.02051 -0.1191 0.7852 0.0674
-6.500 -0.0752 0.02723 0.01928 -0.1193 0.7790 0.0736
-6.250 -0.0512 0.02723 0.01917 -0.1188 0.7713 0.0803
-6.000 -0.0251 0.02686 0.01865 -0.1186 0.7644 0.0865
-5.750 0.0026 0.02632 0.01789 -0.1187 0.7581 0.0919
-5.500 0.0231 0.02532 0.01647 -0.1174 0.7502 0.0959
-5.250 0.0547 0.02464 0.01571 -0.1182 0.7447 0.0999
-5.000 0.0744 0.02422 0.01519 -0.1167 0.7366 0.1035
-4.750 0.1029 0.02349 0.01417 -0.1168 0.7304 0.1079
-4.500 0.1285 0.02290 0.01335 -0.1163 0.7237 0.1125
-4.250 0.1521 0.02260 0.01303 -0.1156 0.7164 0.1173
-4.000 0.1844 0.02208 0.01229 -0.1163 0.7111 0.1241
-3.750 0.2031 0.02180 0.01194 -0.1146 0.7032 0.1291
-3.500 0.2307 0.02155 0.01162 -0.1145 0.6970 0.1365
-3.250 0.2558 0.02132 0.01128 -0.1139 0.6906 0.1447
-3.000 0.2779 0.02123 0.01114 -0.1128 0.6835 0.1529
-2.750 0.3084 0.02101 0.01080 -0.1132 0.6782 0.1621
-2.500 0.3274 0.02099 0.01073 -0.1115 0.6709 0.1712
-2.250 0.3528 0.02091 0.01060 -0.1110 0.6646 0.1810
-2.000 0.3797 0.02084 0.01043 -0.1108 0.6591 0.1930
-1.750 0.3987 0.02088 0.01042 -0.1091 0.6520 0.2046
-1.500 0.4258 0.02078 0.01029 -0.1090 0.6467 0.2164
-1.250 0.4479 0.02074 0.01021 -0.1079 0.6406 0.2269
-1.000 0.4698 0.02072 0.01016 -0.1068 0.6342 0.2381
-0.750 0.4991 0.02059 0.00998 -0.1070 0.6293 0.2503
-0.500 0.5185 0.02064 0.01003 -0.1054 0.6229 0.2604
-0.250 0.5426 0.02063 0.01000 -0.1047 0.6171 0.2718
0.000 0.5735 0.02054 0.00985 -0.1053 0.6126 0.2853
0.250 0.5902 0.02066 0.01002 -0.1033 0.6060 0.2972
0.500 0.6149 0.02068 0.01002 -0.1027 0.6006 0.3120
1.000 0.6595 0.02076 0.01013 -0.1008 0.5898 0.3474
1.250 0.6824 0.02074 0.01014 -0.1000 0.5846 0.3719
1.500 0.7097 0.02058 0.01000 -0.1000 0.5805 0.4096
2.000 0.8918 0.02024 0.01081 -0.1262 0.5670 1.0000
2.250 0.9101 0.02045 0.01092 -0.1245 0.5622 1.0000
2.500 0.9216 0.02075 0.01120 -0.1215 0.5565 1.0000
2.750 0.9408 0.02094 0.01128 -0.1200 0.5517 1.0000
3.000 0.9630 0.02111 0.01134 -0.1190 0.5475 1.0000
3.250 0.9705 0.02149 0.01174 -0.1154 0.5417 1.0000
3.500 0.9876 0.02173 0.01192 -0.1135 0.5368 1.0000
3.750 1.0124 0.02187 0.01195 -0.1130 0.5327 1.0000
4.000 1.0188 0.02229 0.01241 -0.1092 0.5271 1.0000
4.250 1.0326 0.02261 0.01270 -0.1067 0.5220 1.0000
4.500 1.0554 0.02279 0.01280 -0.1059 0.5177 1.0000
4.750 1.0680 0.02316 0.01317 -0.1033 0.5130 1.0000
5.000 1.0744 0.02358 0.01361 -0.0996 0.5075 1.0000
5.250 1.0933 0.02381 0.01380 -0.0981 0.5029 1.0000
5.500 1.1154 0.02405 0.01398 -0.0972 0.4988 1.0000
5.750 1.1120 0.02461 0.01463 -0.0918 0.4931 1.0000
6.000 1.1262 0.02495 0.01496 -0.0896 0.4882 1.0000
6.250 1.1533 0.02510 0.01504 -0.0896 0.4841 1.0000
6.500 1.1505 0.02579 0.01582 -0.0846 0.4786 1.0000
6.750 1.1599 0.02628 0.01636 -0.0817 0.4733 1.0000
7.000 1.1834 0.02647 0.01651 -0.0812 0.4690 1.0000
7.250 1.1874 0.02715 0.01724 -0.0776 0.4636 1.0000
7.500 1.1923 0.02783 0.01798 -0.0743 0.4578 1.0000
7.750 1.2140 0.02805 0.01819 -0.0735 0.4533 1.0000
8.000 1.2176 0.02883 0.01904 -0.0702 0.4476 1.0000
8.250 1.2209 0.02962 0.01989 -0.0669 0.4411 1.0000
8.500 1.2463 0.02961 0.01982 -0.0666 0.4359 1.0000
8.750 1.2342 0.03110 0.02146 -0.0617 0.4287 1.0000
9.000 1.2470 0.03162 0.02200 -0.0599 0.4227 1.0000
9.250 1.2561 0.03238 0.02280 -0.0578 0.4171 1.0000
9.500 1.2524 0.03385 0.02438 -0.0545 0.4106 1.0000
9.750 1.2711 0.03420 0.02473 -0.0536 0.4058 1.0000
10.000 1.2684 0.03578 0.02642 -0.0507 0.3997 1.0000
10.250 1.2704 0.03715 0.02789 -0.0484 0.3935 1.0000
10.500 1.2941 0.03721 0.02794 -0.0480 0.3892 1.0000
10.750 1.2764 0.04002 0.03091 -0.0445 0.3819 1.0000
11.000 1.2870 0.04097 0.03190 -0.0432 0.3763 1.0000
11.250 1.2960 0.04207 0.03305 -0.0418 0.3709 1.0000
11.500 1.2837 0.04489 0.03602 -0.0394 0.3637 1.0000
11.750 1.3041 0.04514 0.03628 -0.0388 0.3592 1.0000
12.000 1.2905 0.04833 0.03961 -0.0367 0.3523 1.0000
12.250 1.2937 0.05011 0.04147 -0.0354 0.3464 1.0000
12.500 1.3228 0.04955 0.04091 -0.0352 0.3426 1.0000
12.750 1.2881 0.05503 0.04657 -0.0329 0.3337 1.0000
13.000 1.3075 0.05530 0.04688 -0.0323 0.3290 1.0000
13.250 1.2907 0.05934 0.05105 -0.0309 0.3215 1.0000
13.500 1.2986 0.06070 0.05245 -0.0302 0.3142 1.0000
13.750 1.2871 0.06437 0.05622 -0.0292 0.3066 1.0000
14.000 1.2925 0.06605 0.05792 -0.0286 0.2984 1.0000
14.250 1.2775 0.07039 0.06238 -0.0280 0.2911 1.0000
14.500 1.2855 0.07181 0.06380 -0.0275 0.2827 1.0000
14.750 1.2646 0.07716 0.06929 -0.0272 0.2751 1.0000
15.000 1.2730 0.07866 0.07081 -0.0269 0.2681 1.0000
15.250 1.2588 0.08335 0.07562 -0.0269 0.2615 1.0000
15.500 1.2571 0.08632 0.07867 -0.0268 0.2542 1.0000
15.750 1.2460 0.09067 0.08311 -0.0271 0.2466 1.0000
16.000 1.2421 0.09413 0.08666 -0.0272 0.2406 1.0000
16.250 1.2415 0.09707 0.08965 -0.0274 0.2336 1.0000
16.500 1.2278 0.10207 0.09477 -0.0281 0.2269 1.0000
16.750 1.2361 0.10373 0.09647 -0.0281 0.2206 1.0000
17.000 1.2137 0.11024 0.10312 -0.0294 0.2142 1.0000
17.250 1.2259 0.11127 0.10415 -0.0294 0.2068 1.0000
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