GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 50,000 Max Cl/Cd: 42.99 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe397-il-50000-n5.txt Download as CSV file: xf-goe397-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3826 0.09953 0.09275 -0.0202 1.0000 0.0766
-7.500 -0.3830 0.09779 0.09112 -0.0224 1.0000 0.0788
-7.250 -0.3808 0.09659 0.09001 -0.0279 1.0000 0.0801
-7.000 -0.3739 0.09307 0.08657 -0.0300 1.0000 0.0810
-6.750 -0.3651 0.08796 0.08149 -0.0259 1.0000 0.0844
-6.500 -0.3579 0.08493 0.07851 -0.0268 1.0000 0.0884
-6.250 -0.3486 0.08314 0.07675 -0.0327 1.0000 0.0935
-6.000 -0.3399 0.07965 0.07332 -0.0347 1.0000 0.0955
-5.750 -0.3342 0.07595 0.06969 -0.0314 1.0000 0.1023
-5.500 -0.3184 0.07389 0.06756 -0.0384 1.0000 0.1093
-5.250 -0.3151 0.06994 0.06374 -0.0341 1.0000 0.1147
-4.750 -0.2922 0.06404 0.05781 -0.0370 1.0000 0.1269
-4.250 -0.2671 0.05833 0.05198 -0.0389 1.0000 0.1408
-4.000 -0.2547 0.05570 0.04928 -0.0394 1.0000 0.1543
-3.750 -0.2446 0.05316 0.04672 -0.0386 1.0000 0.1705
-3.250 -0.1736 0.04392 0.03645 -0.0466 1.0000 0.0772
-3.000 -0.1353 0.04026 0.03240 -0.0505 0.9936 0.0750
-2.750 -0.0926 0.03716 0.02867 -0.0547 0.9864 0.0788
-2.500 -0.0553 0.03427 0.02532 -0.0575 0.9789 0.0768
-2.250 -0.0178 0.03181 0.02236 -0.0600 0.9713 0.0755
-2.000 0.0204 0.02971 0.01973 -0.0623 0.9644 0.0751
-1.750 0.0566 0.02812 0.01762 -0.0641 0.9564 0.0779
-1.500 0.0914 0.02689 0.01607 -0.0659 0.9486 0.0843
-1.250 0.1289 0.02565 0.01444 -0.0677 0.9415 0.0846
-1.000 0.1631 0.02466 0.01313 -0.0689 0.9337 0.0849
-0.750 0.2021 0.02381 0.01197 -0.0709 0.9272 0.0856
-0.500 0.2378 0.02316 0.01106 -0.0723 0.9195 0.0870
-0.250 0.2766 0.02258 0.01031 -0.0743 0.9131 0.0893
0.000 0.3094 0.02219 0.00977 -0.0753 0.9043 0.0925
0.250 0.3475 0.02177 0.00929 -0.0772 0.8976 0.0981
0.500 0.3786 0.02152 0.00901 -0.0779 0.8872 0.1091
0.750 0.4127 0.02101 0.00874 -0.0791 0.8771 0.1554
1.250 0.4898 0.01914 0.00835 -0.0828 0.8576 1.0000
1.500 0.5191 0.01933 0.00842 -0.0828 0.8456 1.0000
1.750 0.5478 0.01954 0.00856 -0.0828 0.8339 1.0000
2.000 0.5763 0.01975 0.00873 -0.0827 0.8226 1.0000
2.250 0.6055 0.01995 0.00891 -0.0826 0.8117 1.0000
2.500 0.6341 0.02016 0.00918 -0.0824 0.8007 1.0000
2.750 0.6596 0.02045 0.00952 -0.0818 0.7882 1.0000
3.000 0.6852 0.02075 0.00990 -0.0812 0.7759 1.0000
3.250 0.7108 0.02105 0.01030 -0.0806 0.7635 1.0000
3.500 0.7366 0.02133 0.01076 -0.0799 0.7510 1.0000
3.750 0.7624 0.02162 0.01119 -0.0792 0.7384 1.0000
4.000 0.7882 0.02189 0.01165 -0.0784 0.7256 1.0000
4.250 0.8137 0.02217 0.01218 -0.0776 0.7123 1.0000
4.500 0.8391 0.02247 0.01272 -0.0767 0.6987 1.0000
4.750 0.8624 0.02258 0.01306 -0.0750 0.6779 1.0000
5.000 0.8854 0.02197 0.01252 -0.0716 0.6412 1.0000
5.250 0.9035 0.02163 0.01222 -0.0680 0.5920 1.0000
5.500 0.9211 0.02166 0.01242 -0.0650 0.5392 1.0000
5.750 0.9367 0.02179 0.01243 -0.0615 0.4532 1.0000
6.000 0.9446 0.02314 0.01284 -0.0575 0.2933 1.0000
6.250 0.9465 0.02609 0.01459 -0.0545 0.1524 1.0000
6.500 0.9557 0.02849 0.01667 -0.0523 0.1144 1.0000
6.750 0.9664 0.03063 0.01871 -0.0503 0.0915 1.0000
7.000 0.9800 0.03256 0.02079 -0.0484 0.0737 1.0000
7.250 0.9955 0.03470 0.02297 -0.0465 0.0626 1.0000
7.500 1.0155 0.03674 0.02513 -0.0451 0.0529 1.0000
7.750 1.0444 0.03934 0.02799 -0.0442 0.0470 1.0000
8.000 1.0661 0.04169 0.03050 -0.0433 0.0412 1.0000
8.250 1.0903 0.04512 0.03420 -0.0425 0.0386 1.0000
8.500 1.1096 0.04863 0.03828 -0.0411 0.0370 1.0000
8.750 1.1228 0.05205 0.04221 -0.0394 0.0349 1.0000
9.000 1.1324 0.05519 0.04580 -0.0378 0.0328 1.0000
9.250 1.1403 0.05844 0.04927 -0.0365 0.0313 1.0000
9.500 1.1438 0.06248 0.05359 -0.0350 0.0305 1.0000
9.750 1.1419 0.06660 0.05804 -0.0331 0.0304 1.0000
10.000 1.1355 0.07057 0.06238 -0.0311 0.0303 1.0000
10.250 1.1247 0.07445 0.06656 -0.0292 0.0303 1.0000
10.500 1.1107 0.07822 0.07055 -0.0275 0.0303 1.0000
10.750 1.0952 0.08225 0.07477 -0.0267 0.0304 1.0000
11.250 1.0575 0.09174 0.08473 -0.0288 0.0308 1.0000
11.500 1.0264 0.09926 0.09248 -0.0337 0.0316 1.0000
11.750 0.9999 0.10831 0.10165 -0.0401 0.0325 1.0000
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Polar data table (+)
Polar graphs
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