GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 624 AIRFOIL (goe624-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.88 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe624-il-1000000-n5.txt Download as CSV file: xf-goe624-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 624 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7103 0.10710 0.10480 -0.0476 1.0000 0.0212
-16.500 -0.7802 0.09103 0.08855 -0.0575 1.0000 0.0213
-16.250 -0.8648 0.07400 0.07129 -0.0688 1.0000 0.0213
-16.000 -0.9589 0.05529 0.05229 -0.0825 1.0000 0.0212
-15.500 -1.0185 0.03394 0.03037 -0.1051 0.9544 0.0213
-15.250 -1.0242 0.03114 0.02738 -0.1058 0.9302 0.0213
-15.000 -1.0240 0.02933 0.02542 -0.1049 0.9119 0.0214
-14.750 -1.0208 0.02803 0.02397 -0.1031 0.8965 0.0215
-14.500 -1.0096 0.02690 0.02271 -0.1020 0.8842 0.0216
-14.250 -0.9952 0.02589 0.02159 -0.1011 0.8728 0.0217
-14.000 -0.9788 0.02496 0.02055 -0.1003 0.8635 0.0219
-13.750 -0.9608 0.02411 0.01959 -0.0996 0.8548 0.0220
-13.500 -0.9413 0.02334 0.01872 -0.0990 0.8476 0.0222
-13.250 -0.9206 0.02263 0.01793 -0.0985 0.8402 0.0223
-12.750 -0.8775 0.02127 0.01638 -0.0975 0.8265 0.0227
-12.500 -0.8552 0.02061 0.01562 -0.0970 0.8195 0.0229
-12.250 -0.8325 0.01998 0.01489 -0.0965 0.8133 0.0230
-12.000 -0.8090 0.01936 0.01419 -0.0961 0.8077 0.0232
-11.750 -0.7850 0.01879 0.01354 -0.0958 0.8017 0.0234
-11.250 -0.7358 0.01774 0.01231 -0.0951 0.7907 0.0237
-11.000 -0.7105 0.01726 0.01175 -0.0948 0.7844 0.0238
-10.750 -0.6851 0.01682 0.01122 -0.0946 0.7779 0.0239
-10.500 -0.6590 0.01639 0.01072 -0.0944 0.7722 0.0240
-10.250 -0.6332 0.01592 0.01018 -0.0941 0.7660 0.0242
-9.750 -0.5820 0.01490 0.00903 -0.0936 0.7517 0.0248
-9.500 -0.5556 0.01451 0.00857 -0.0934 0.7422 0.0250
-9.250 -0.5287 0.01415 0.00815 -0.0933 0.7326 0.0252
-9.000 -0.5018 0.01383 0.00775 -0.0932 0.7229 0.0254
-8.750 -0.4744 0.01353 0.00738 -0.0931 0.7120 0.0257
-8.500 -0.4471 0.01324 0.00702 -0.0930 0.7014 0.0259
-8.250 -0.4196 0.01298 0.00668 -0.0929 0.6906 0.0262
-8.000 -0.3918 0.01271 0.00635 -0.0928 0.6820 0.0265
-7.750 -0.3639 0.01247 0.00604 -0.0928 0.6734 0.0267
-7.500 -0.3359 0.01223 0.00575 -0.0928 0.6665 0.0270
-7.250 -0.3077 0.01200 0.00547 -0.0928 0.6594 0.0273
-7.000 -0.2795 0.01181 0.00521 -0.0928 0.6523 0.0275
-6.750 -0.2510 0.01161 0.00496 -0.0928 0.6455 0.0277
-6.500 -0.2228 0.01139 0.00469 -0.0928 0.6382 0.0281
-6.250 -0.1945 0.01115 0.00442 -0.0929 0.6325 0.0286
-6.000 -0.1659 0.01094 0.00419 -0.0929 0.6270 0.0292
-5.750 -0.1373 0.01077 0.00398 -0.0930 0.6212 0.0297
-5.500 -0.1086 0.01062 0.00379 -0.0931 0.6157 0.0302
-5.250 -0.0796 0.01047 0.00361 -0.0932 0.6102 0.0307
-5.000 -0.0508 0.01034 0.00345 -0.0933 0.6038 0.0312
-4.750 -0.0220 0.01023 0.00330 -0.0934 0.5980 0.0317
-4.500 0.0070 0.01007 0.00313 -0.0936 0.5928 0.0327
-4.250 0.0360 0.00994 0.00298 -0.0937 0.5870 0.0337
-3.750 0.0940 0.00973 0.00273 -0.0940 0.5761 0.0368
-3.500 0.1229 0.00961 0.00261 -0.0941 0.5694 0.0400
-3.250 0.1516 0.00950 0.00250 -0.0942 0.5625 0.0470
-3.000 0.1805 0.00937 0.00242 -0.0944 0.5552 0.0599
-2.750 0.2093 0.00931 0.00237 -0.0946 0.5472 0.0680
-2.500 0.2385 0.00927 0.00232 -0.0947 0.5402 0.0733
-2.250 0.2674 0.00924 0.00227 -0.0949 0.5316 0.0778
-2.000 0.2964 0.00922 0.00223 -0.0951 0.5234 0.0817
-1.750 0.3251 0.00922 0.00220 -0.0952 0.5131 0.0858
-1.500 0.3539 0.00921 0.00218 -0.0954 0.5027 0.0907
-1.250 0.3824 0.00924 0.00216 -0.0955 0.4918 0.0952
-1.000 0.4110 0.00924 0.00215 -0.0956 0.4816 0.1020
-0.750 0.4396 0.00926 0.00215 -0.0957 0.4732 0.1082
-0.500 0.4681 0.00927 0.00215 -0.0959 0.4643 0.1171
-0.250 0.4966 0.00927 0.00217 -0.0960 0.4567 0.1286
0.000 0.5249 0.00925 0.00219 -0.0961 0.4488 0.1522
0.250 0.5530 0.00920 0.00222 -0.0963 0.4423 0.1893
0.500 0.5815 0.00916 0.00225 -0.0964 0.4373 0.2192
0.750 0.6098 0.00915 0.00230 -0.0966 0.4316 0.2475
1.000 0.6378 0.00916 0.00236 -0.0967 0.4260 0.2804
1.250 0.6663 0.00910 0.00241 -0.0969 0.4219 0.3210
1.500 0.6945 0.00904 0.00247 -0.0971 0.4177 0.3729
1.750 0.7221 0.00894 0.00255 -0.0972 0.4133 0.4462
2.000 0.7494 0.00884 0.00264 -0.0973 0.4087 0.5295
2.250 0.7769 0.00864 0.00273 -0.0973 0.4056 0.6348
2.500 0.8028 0.00840 0.00285 -0.0970 0.4013 0.7634
2.750 0.8260 0.00826 0.00299 -0.0959 0.3959 0.8690
3.000 0.8495 0.00826 0.00313 -0.0947 0.3908 0.9561
3.250 0.8879 0.00834 0.00321 -0.0970 0.3863 0.9899
3.500 0.9223 0.00848 0.00330 -0.0986 0.3806 0.9995
3.750 0.9484 0.00865 0.00342 -0.0984 0.3747 1.0000
4.000 0.9754 0.00875 0.00351 -0.0983 0.3710 1.0000
4.250 1.0023 0.00887 0.00360 -0.0982 0.3671 1.0000
4.500 1.0289 0.00900 0.00372 -0.0980 0.3633 1.0000
4.750 1.0553 0.00916 0.00384 -0.0979 0.3595 1.0000
5.000 1.0819 0.00929 0.00397 -0.0978 0.3564 1.0000
5.250 1.1089 0.00941 0.00409 -0.0977 0.3532 1.0000
5.500 1.1355 0.00955 0.00422 -0.0976 0.3494 1.0000
5.750 1.1616 0.00972 0.00436 -0.0974 0.3452 1.0000
6.000 1.1872 0.00991 0.00453 -0.0972 0.3410 1.0000
6.250 1.2137 0.01005 0.00467 -0.0971 0.3369 1.0000
6.500 1.2390 0.01025 0.00484 -0.0968 0.3300 1.0000
6.750 1.2636 0.01048 0.00504 -0.0965 0.3232 1.0000
7.000 1.2888 0.01067 0.00522 -0.0962 0.3170 1.0000
7.250 1.3126 0.01092 0.00544 -0.0957 0.3103 1.0000
7.500 1.3368 0.01114 0.00565 -0.0952 0.3035 1.0000
7.750 1.3589 0.01146 0.00592 -0.0945 0.2942 1.0000
8.000 1.3812 0.01175 0.00618 -0.0938 0.2849 1.0000
8.250 1.4016 0.01211 0.00650 -0.0927 0.2755 1.0000
8.500 1.4208 0.01245 0.00681 -0.0915 0.2665 1.0000
8.750 1.4386 0.01282 0.00716 -0.0899 0.2584 1.0000
9.000 1.4551 0.01328 0.00758 -0.0883 0.2491 1.0000
9.250 1.4726 0.01373 0.00800 -0.0869 0.2402 1.0000
9.500 1.4882 0.01428 0.00852 -0.0853 0.2306 1.0000
9.750 1.5033 0.01489 0.00909 -0.0837 0.2206 1.0000
10.000 1.5195 0.01547 0.00965 -0.0823 0.2125 1.0000
10.500 1.5503 0.01678 0.01094 -0.0796 0.1982 1.0000
11.000 1.5787 0.01832 0.01245 -0.0769 0.1843 1.0000
11.250 1.5908 0.01926 0.01337 -0.0754 0.1770 1.0000
11.500 1.6047 0.02012 0.01423 -0.0743 0.1714 1.0000
11.750 1.6172 0.02109 0.01520 -0.0730 0.1655 1.0000
12.000 1.6286 0.02217 0.01628 -0.0717 0.1598 1.0000
12.250 1.6423 0.02311 0.01724 -0.0707 0.1559 1.0000
12.500 1.6529 0.02429 0.01843 -0.0695 0.1509 1.0000
12.750 1.6632 0.02552 0.01968 -0.0684 0.1462 1.0000
13.000 1.6746 0.02669 0.02087 -0.0674 0.1415 1.0000
13.250 1.6804 0.02831 0.02249 -0.0660 0.1350 1.0000
13.500 1.6879 0.02985 0.02403 -0.0649 0.1282 1.0000
13.750 1.6902 0.03183 0.02600 -0.0635 0.1196 1.0000
14.000 1.6891 0.03416 0.02829 -0.0620 0.1093 1.0000
14.250 1.6853 0.03684 0.03095 -0.0606 0.0987 1.0000
14.500 1.6828 0.03951 0.03362 -0.0595 0.0915 1.0000
14.750 1.6821 0.04209 0.03621 -0.0585 0.0864 1.0000
15.000 1.6801 0.04487 0.03901 -0.0577 0.0821 1.0000
15.250 1.6804 0.04748 0.04168 -0.0570 0.0788 1.0000
15.500 1.6806 0.05015 0.04440 -0.0564 0.0758 1.0000
15.750 1.6788 0.05306 0.04734 -0.0559 0.0731 1.0000
16.000 1.6782 0.05589 0.05022 -0.0555 0.0707 1.0000
16.250 1.6777 0.05878 0.05317 -0.0551 0.0680 1.0000
16.500 1.6729 0.06217 0.05660 -0.0548 0.0648 1.0000
16.750 1.6693 0.06546 0.05994 -0.0546 0.0622 1.0000
17.000 1.6663 0.06872 0.06326 -0.0545 0.0591 1.0000
17.250 1.6589 0.07258 0.06715 -0.0544 0.0558 1.0000
17.500 1.6529 0.07632 0.07094 -0.0545 0.0520 1.0000
17.750 1.6431 0.08054 0.07520 -0.0547 0.0482 1.0000
18.000 1.6327 0.08494 0.07963 -0.0550 0.0439 1.0000
18.250 1.6216 0.08949 0.08422 -0.0554 0.0397 1.0000
18.500 1.6089 0.09429 0.08905 -0.0560 0.0353 1.0000
18.750 1.5956 0.09920 0.09400 -0.0566 0.0310 1.0000
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