GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 500,000 Max Cl/Cd: 109.96 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe397-il-500000.txt Download as CSV file: xf-goe397-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 397 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3907 0.08829 0.08607 -0.0184 1.0000 0.0155
-7.500 -0.3888 0.08591 0.08372 -0.0186 1.0000 0.0160
-7.250 -0.3869 0.08344 0.08128 -0.0192 1.0000 0.0167
-7.000 -0.3809 0.08049 0.07836 -0.0210 1.0000 0.0172
-6.750 -0.3735 0.07736 0.07524 -0.0233 1.0000 0.0177
-6.500 -0.3611 0.07421 0.07210 -0.0274 1.0000 0.0189
-6.250 -0.3448 0.07092 0.06880 -0.0326 1.0000 0.0193
-6.000 -0.3318 0.06758 0.06544 -0.0351 1.0000 0.0195
-5.750 -0.3185 0.06420 0.06203 -0.0371 0.9996 0.0195
-5.500 -0.2793 0.05850 0.05624 -0.0453 0.9953 0.0196
-5.250 -0.2462 0.04991 0.04751 -0.0539 0.9889 0.0201
-5.000 -0.2186 0.04654 0.04410 -0.0575 0.9842 0.0209
-4.750 -0.1888 0.04427 0.04178 -0.0606 0.9777 0.0227
-4.500 -0.1434 0.04049 0.03780 -0.0663 0.9718 0.0266
-4.250 -0.1008 0.03692 0.03396 -0.0703 0.9632 0.0274
-4.000 -0.0638 0.03262 0.02937 -0.0737 0.9541 0.0276
-3.750 -0.0378 0.02599 0.02244 -0.0768 0.9401 0.0294
-3.500 -0.0105 0.02472 0.02107 -0.0777 0.9249 0.0314
-3.250 0.0172 0.02293 0.01904 -0.0779 0.9086 0.0354
-3.000 0.0482 0.02287 0.01860 -0.0770 0.8930 0.0387
-1.500 0.0939 0.01990 0.01595 -0.0665 0.7930 0.0443
-1.250 0.2220 0.01131 0.00515 -0.0726 0.7936 0.0453
-1.000 0.2484 0.01044 0.00409 -0.0719 0.7812 0.0435
-0.750 0.2746 0.00992 0.00346 -0.0713 0.7695 0.0431
-0.500 0.3008 0.00951 0.00296 -0.0708 0.7589 0.0429
-0.250 0.3271 0.00920 0.00262 -0.0704 0.7482 0.0439
0.000 0.3534 0.00892 0.00229 -0.0699 0.7383 0.0442
0.250 0.3796 0.00868 0.00200 -0.0694 0.7292 0.0439
0.500 0.4061 0.00847 0.00178 -0.0690 0.7198 0.0442
0.750 0.4326 0.00832 0.00160 -0.0686 0.7112 0.0455
1.000 0.4591 0.00823 0.00147 -0.0682 0.7028 0.0479
1.250 0.4859 0.00816 0.00138 -0.0679 0.6942 0.0511
1.500 0.5127 0.00813 0.00133 -0.0676 0.6869 0.0578
1.750 0.5367 0.00747 0.00147 -0.0671 0.6790 0.3785
2.000 0.5890 0.00613 0.00152 -0.0729 0.6690 1.0000
2.250 0.6144 0.00624 0.00155 -0.0722 0.6542 1.0000
2.500 0.6401 0.00635 0.00161 -0.0717 0.6430 1.0000
2.750 0.6657 0.00647 0.00168 -0.0711 0.6305 1.0000
3.000 0.6909 0.00658 0.00177 -0.0705 0.6113 1.0000
3.250 0.7158 0.00672 0.00184 -0.0698 0.5903 1.0000
3.500 0.7413 0.00683 0.00194 -0.0692 0.5696 1.0000
3.750 0.7664 0.00697 0.00204 -0.0686 0.5433 1.0000
4.250 0.8097 0.00791 0.00242 -0.0662 0.4033 1.0000
4.500 0.8297 0.00870 0.00279 -0.0650 0.3163 1.0000
4.750 0.8428 0.01041 0.00355 -0.0630 0.1213 1.0000
5.000 0.8636 0.01123 0.00408 -0.0620 0.0703 1.0000
5.250 0.8868 0.01172 0.00455 -0.0612 0.0561 1.0000
5.500 0.9104 0.01215 0.00500 -0.0604 0.0463 1.0000
5.750 0.9331 0.01270 0.00554 -0.0595 0.0347 1.0000
6.000 0.9550 0.01336 0.00621 -0.0585 0.0268 1.0000
6.250 0.9774 0.01393 0.00679 -0.0575 0.0226 1.0000
6.500 0.9953 0.01509 0.00808 -0.0558 0.0200 1.0000
6.750 1.0164 0.01582 0.00889 -0.0546 0.0187 1.0000
7.000 1.0373 0.01655 0.00969 -0.0534 0.0171 1.0000
7.250 1.0586 0.01719 0.01035 -0.0525 0.0154 1.0000
7.500 1.0740 0.01883 0.01210 -0.0505 0.0143 1.0000
7.750 1.0896 0.02111 0.01455 -0.0485 0.0136 1.0000
8.000 1.1103 0.02232 0.01593 -0.0474 0.0132 1.0000
8.250 1.1303 0.02395 0.01774 -0.0461 0.0127 1.0000
8.500 1.1492 0.02620 0.02023 -0.0446 0.0123 1.0000
8.750 1.1660 0.02898 0.02332 -0.0430 0.0121 1.0000
9.000 1.1822 0.03099 0.02558 -0.0414 0.0115 1.0000
9.250 1.1966 0.03296 0.02777 -0.0398 0.0110 1.0000
9.500 1.1963 0.03926 0.03470 -0.0362 0.0115 1.0000
9.750 1.1900 0.04506 0.04097 -0.0327 0.0121 1.0000
10.000 1.1794 0.05016 0.04643 -0.0293 0.0126 1.0000
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Polar data table (+)
Polar graphs
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