GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 500,000 Max Cl/Cd: 95.23 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe493-il-500000-n5.txt Download as CSV file: xf-goe493-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7567 0.08678 0.08308 -0.0733 1.0000 0.0104
-16.250 -0.7732 0.08088 0.07710 -0.0760 1.0000 0.0104
-16.000 -0.7909 0.07501 0.07114 -0.0786 1.0000 0.0104
-15.750 -0.8085 0.06931 0.06534 -0.0812 1.0000 0.0105
-15.500 -0.8314 0.06321 0.05914 -0.0838 1.0000 0.0104
-15.250 -0.8472 0.05826 0.05409 -0.0857 1.0000 0.0105
-15.000 -0.8668 0.05315 0.04888 -0.0875 1.0000 0.0105
-14.750 -0.8843 0.04870 0.04433 -0.0887 1.0000 0.0105
-14.250 -0.9005 0.03941 0.03481 -0.0955 0.9972 0.0108
-14.000 -0.8945 0.03542 0.03070 -0.1003 0.9926 0.0110
-13.750 -0.8858 0.03212 0.02727 -0.1043 0.9876 0.0112
-13.500 -0.8710 0.02958 0.02462 -0.1080 0.9839 0.0115
-13.250 -0.8591 0.02752 0.02245 -0.1100 0.9772 0.0118
-13.000 -0.8411 0.02571 0.02051 -0.1125 0.9733 0.0122
-12.750 -0.8275 0.02425 0.01894 -0.1133 0.9660 0.0125
-12.500 -0.8051 0.02303 0.01759 -0.1149 0.9621 0.0129
-12.250 -0.7838 0.02197 0.01642 -0.1158 0.9572 0.0133
-12.000 -0.7644 0.02091 0.01526 -0.1161 0.9510 0.0137
-11.750 -0.7393 0.01986 0.01413 -0.1173 0.9470 0.0143
-11.500 -0.7193 0.01910 0.01330 -0.1171 0.9403 0.0149
-11.250 -0.6952 0.01840 0.01250 -0.1174 0.9349 0.0158
-11.000 -0.6692 0.01776 0.01176 -0.1180 0.9304 0.0166
-10.750 -0.6511 0.01715 0.01108 -0.1170 0.9230 0.0175
-10.500 -0.6281 0.01654 0.01041 -0.1168 0.9174 0.0187
-10.250 -0.6065 0.01604 0.00983 -0.1162 0.9117 0.0200
-10.000 -0.5855 0.01558 0.00930 -0.1154 0.9052 0.0214
-9.750 -0.5624 0.01508 0.00875 -0.1150 0.9000 0.0234
-9.500 -0.5414 0.01468 0.00830 -0.1141 0.8941 0.0260
-9.250 -0.5198 0.01425 0.00783 -0.1133 0.8883 0.0292
-9.000 -0.4962 0.01383 0.00736 -0.1129 0.8834 0.0332
-8.750 -0.4748 0.01347 0.00698 -0.1119 0.8777 0.0375
-8.500 -0.4522 0.01310 0.00659 -0.1112 0.8721 0.0431
-8.250 -0.4281 0.01273 0.00621 -0.1108 0.8673 0.0503
-8.000 -0.4059 0.01240 0.00589 -0.1099 0.8617 0.0582
-7.750 -0.3822 0.01210 0.00559 -0.1093 0.8561 0.0664
-7.500 -0.3569 0.01185 0.00531 -0.1090 0.8515 0.0742
-7.250 -0.3331 0.01162 0.00508 -0.1084 0.8458 0.0821
-7.000 -0.3085 0.01138 0.00483 -0.1079 0.8403 0.0890
-6.750 -0.2824 0.01120 0.00461 -0.1077 0.8356 0.0960
-6.500 -0.2584 0.01097 0.00440 -0.1071 0.8299 0.1041
-6.250 -0.2328 0.01081 0.00419 -0.1067 0.8245 0.1109
-6.000 -0.2072 0.01060 0.00397 -0.1064 0.8195 0.1180
-5.750 -0.1821 0.01045 0.00380 -0.1059 0.8137 0.1244
-5.500 -0.1569 0.01025 0.00360 -0.1055 0.8079 0.1327
-5.250 -0.1309 0.01010 0.00342 -0.1052 0.8027 0.1419
-5.000 -0.1058 0.00992 0.00326 -0.1047 0.7966 0.1527
-4.750 -0.0802 0.00975 0.00310 -0.1043 0.7908 0.1645
-4.500 -0.0546 0.00960 0.00295 -0.1040 0.7850 0.1771
-4.250 -0.0291 0.00945 0.00281 -0.1036 0.7784 0.1901
-4.000 -0.0034 0.00930 0.00267 -0.1032 0.7726 0.2071
-3.750 0.0220 0.00914 0.00255 -0.1028 0.7663 0.2247
-3.500 0.0475 0.00900 0.00244 -0.1024 0.7597 0.2432
-3.250 0.0731 0.00887 0.00233 -0.1020 0.7532 0.2644
-3.000 0.0982 0.00871 0.00225 -0.1015 0.7461 0.2902
-2.750 0.1238 0.00860 0.00216 -0.1011 0.7398 0.3156
-2.500 0.1492 0.00848 0.00211 -0.1007 0.7328 0.3389
-2.250 0.1749 0.00841 0.00205 -0.1002 0.7258 0.3610
-2.000 0.2003 0.00832 0.00201 -0.0998 0.7184 0.3843
-1.750 0.2259 0.00826 0.00198 -0.0993 0.7110 0.4059
-1.500 0.2517 0.00822 0.00196 -0.0989 0.7040 0.4244
-1.250 0.2771 0.00820 0.00194 -0.0984 0.6953 0.4416
-1.000 0.3025 0.00818 0.00194 -0.0979 0.6862 0.4587
-0.750 0.3273 0.00819 0.00194 -0.0973 0.6767 0.4776
-0.500 0.3524 0.00817 0.00195 -0.0967 0.6674 0.4965
-0.250 0.3774 0.00818 0.00196 -0.0961 0.6587 0.5130
0.000 0.4022 0.00820 0.00198 -0.0955 0.6487 0.5268
0.250 0.4270 0.00822 0.00201 -0.0949 0.6393 0.5402
0.750 0.4764 0.00829 0.00208 -0.0936 0.6211 0.5670
1.000 0.5008 0.00833 0.00213 -0.0929 0.6135 0.5825
1.250 0.5257 0.00834 0.00219 -0.0923 0.6055 0.5989
1.500 0.5499 0.00838 0.00225 -0.0915 0.5985 0.6143
1.750 0.5749 0.00840 0.00231 -0.0910 0.5918 0.6299
2.250 0.6231 0.00846 0.00247 -0.0894 0.5784 0.6650
2.500 0.6468 0.00849 0.00257 -0.0886 0.5711 0.6860
2.750 0.6698 0.00853 0.00267 -0.0876 0.5642 0.7097
3.000 0.6930 0.00856 0.00278 -0.0866 0.5565 0.7342
3.250 0.7150 0.00862 0.00289 -0.0854 0.5493 0.7595
3.500 0.7375 0.00865 0.00301 -0.0843 0.5410 0.7847
3.750 0.7578 0.00872 0.00313 -0.0827 0.5302 0.8109
4.000 0.7771 0.00879 0.00326 -0.0809 0.5184 0.8416
4.250 0.7998 0.00883 0.00341 -0.0798 0.5063 0.8814
4.500 0.8450 0.00907 0.00368 -0.0838 0.4863 0.9358
4.750 0.8980 0.00943 0.00397 -0.0898 0.4591 0.9954
5.000 0.9158 0.00971 0.00417 -0.0879 0.4402 1.0000
5.250 0.9278 0.00996 0.00434 -0.0848 0.4210 1.0000
5.500 0.9375 0.01031 0.00457 -0.0812 0.3950 1.0000
5.750 0.9478 0.01071 0.00484 -0.0779 0.3693 1.0000
6.000 0.9584 0.01116 0.00516 -0.0748 0.3454 1.0000
6.250 0.9721 0.01156 0.00548 -0.0723 0.3264 1.0000
6.500 0.9863 0.01197 0.00582 -0.0700 0.3088 1.0000
6.750 1.0010 0.01239 0.00618 -0.0677 0.2915 1.0000
7.000 1.0142 0.01289 0.00658 -0.0653 0.2693 1.0000
7.250 1.0252 0.01350 0.00705 -0.0627 0.2388 1.0000
7.500 1.0228 0.01475 0.00791 -0.0581 0.1706 1.0000
7.750 1.0298 0.01565 0.00865 -0.0550 0.1407 1.0000
8.000 1.0380 0.01654 0.00940 -0.0523 0.1117 1.0000
8.250 1.0449 0.01752 0.01022 -0.0495 0.0836 1.0000
8.500 1.0557 0.01833 0.01096 -0.0473 0.0680 1.0000
8.750 1.0671 0.01915 0.01172 -0.0453 0.0543 1.0000
9.000 1.0785 0.01999 0.01251 -0.0434 0.0451 1.0000
9.250 1.0915 0.02076 0.01328 -0.0417 0.0409 1.0000
9.500 1.1054 0.02150 0.01404 -0.0401 0.0386 1.0000
9.750 1.1180 0.02234 0.01489 -0.0385 0.0364 1.0000
10.000 1.1300 0.02323 0.01581 -0.0369 0.0348 1.0000
10.250 1.1433 0.02407 0.01669 -0.0355 0.0338 1.0000
10.500 1.1561 0.02496 0.01764 -0.0342 0.0329 1.0000
10.750 1.1685 0.02590 0.01863 -0.0328 0.0319 1.0000
11.000 1.1796 0.02695 0.01972 -0.0314 0.0309 1.0000
11.250 1.1895 0.02811 0.02091 -0.0300 0.0299 1.0000
11.500 1.1979 0.02941 0.02226 -0.0285 0.0289 1.0000
11.750 1.2057 0.03081 0.02371 -0.0271 0.0282 1.0000
12.000 1.2173 0.03194 0.02491 -0.0261 0.0275 1.0000
12.250 1.2268 0.03326 0.02630 -0.0250 0.0269 1.0000
12.500 1.2363 0.03463 0.02773 -0.0239 0.0262 1.0000
12.750 1.2453 0.03608 0.02924 -0.0229 0.0256 1.0000
13.000 1.2531 0.03765 0.03087 -0.0220 0.0249 1.0000
13.250 1.2599 0.03935 0.03263 -0.0211 0.0242 1.0000
13.500 1.2647 0.04129 0.03461 -0.0202 0.0235 1.0000
13.750 1.2683 0.04339 0.03678 -0.0193 0.0229 1.0000
14.000 1.2789 0.04488 0.03835 -0.0188 0.0222 1.0000
14.250 1.2844 0.04687 0.04042 -0.0182 0.0218 1.0000
14.500 1.2927 0.04864 0.04225 -0.0177 0.0210 1.0000
14.750 1.2989 0.05065 0.04433 -0.0173 0.0204 1.0000
15.000 1.3050 0.05269 0.04644 -0.0170 0.0198 1.0000
15.250 1.3086 0.05505 0.04885 -0.0166 0.0193 1.0000
15.500 1.3110 0.05756 0.05142 -0.0164 0.0188 1.0000
15.750 1.3142 0.06003 0.05397 -0.0162 0.0184 1.0000
16.000 1.3185 0.06242 0.05646 -0.0161 0.0179 1.0000
16.250 1.3228 0.06485 0.05897 -0.0161 0.0173 1.0000
16.500 1.3263 0.06740 0.06160 -0.0162 0.0167 1.0000
16.750 1.3289 0.07009 0.06437 -0.0163 0.0162 1.0000
17.000 1.3323 0.07270 0.06704 -0.0165 0.0157 1.0000
17.250 1.3330 0.07570 0.07011 -0.0168 0.0153 1.0000
17.500 1.3323 0.07892 0.07339 -0.0173 0.0149 1.0000
17.750 1.3323 0.08209 0.07666 -0.0177 0.0146 1.0000
18.000 1.3333 0.08515 0.07981 -0.0182 0.0140 1.0000
18.250 1.3325 0.08847 0.08323 -0.0189 0.0136 1.0000
18.500 1.3322 0.09180 0.08664 -0.0196 0.0132 1.0000
18.750 1.3305 0.09536 0.09028 -0.0205 0.0128 1.0000
19.000 1.3286 0.09900 0.09400 -0.0215 0.0125 1.0000
19.250 1.3256 0.10285 0.09793 -0.0226 0.0122 1.0000
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