GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 624 AIRFOIL (goe624-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.86 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe624-il-1000000.txt Download as CSV file: xf-goe624-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7634 0.06563 0.06323 -0.0748 1.0000 0.0251
-14.500 -0.8345 0.04706 0.04429 -0.0928 1.0000 0.0250
-14.250 -0.8545 0.03929 0.03628 -0.1019 1.0000 0.0250
-14.000 -0.8583 0.03517 0.03197 -0.1065 0.9852 0.0251
-13.750 -0.8582 0.03270 0.02930 -0.1072 0.9604 0.0252
-13.500 -0.8614 0.03120 0.02762 -0.1046 0.9393 0.0253
-13.250 -0.8541 0.02988 0.02612 -0.1032 0.9244 0.0254
-13.000 -0.8415 0.02885 0.02493 -0.1021 0.9120 0.0256
-12.750 -0.8341 0.02698 0.02282 -0.1008 0.9003 0.0258
-12.500 -0.8245 0.02498 0.02065 -0.0996 0.8896 0.0261
-12.250 -0.8070 0.02386 0.01944 -0.0988 0.8811 0.0264
-12.000 -0.7873 0.02297 0.01847 -0.0981 0.8728 0.0266
-11.750 -0.7663 0.02218 0.01758 -0.0975 0.8654 0.0268
-11.500 -0.7444 0.02143 0.01674 -0.0970 0.8579 0.0270
-11.250 -0.7221 0.02074 0.01594 -0.0965 0.8506 0.0273
-11.000 -0.6988 0.02003 0.01515 -0.0961 0.8440 0.0275
-10.750 -0.6754 0.01936 0.01438 -0.0956 0.8370 0.0278
-10.500 -0.6515 0.01874 0.01364 -0.0952 0.8306 0.0281
-10.250 -0.6267 0.01811 0.01294 -0.0949 0.8246 0.0283
-10.000 -0.6018 0.01754 0.01227 -0.0945 0.8179 0.0286
-9.750 -0.5763 0.01707 0.01170 -0.0942 0.8111 0.0289
-9.500 -0.5500 0.01664 0.01119 -0.0940 0.8034 0.0292
-9.250 -0.5239 0.01625 0.01069 -0.0937 0.7955 0.0294
-9.000 -0.4985 0.01557 0.00993 -0.0934 0.7882 0.0296
-8.750 -0.4745 0.01470 0.00897 -0.0930 0.7801 0.0301
-8.500 -0.4485 0.01415 0.00837 -0.0928 0.7724 0.0305
-8.250 -0.4218 0.01372 0.00789 -0.0926 0.7643 0.0308
-8.000 -0.3948 0.01336 0.00747 -0.0924 0.7570 0.0312
-7.750 -0.3673 0.01300 0.00707 -0.0924 0.7497 0.0316
-7.500 -0.3399 0.01268 0.00668 -0.0922 0.7421 0.0320
-7.250 -0.3120 0.01236 0.00632 -0.0922 0.7346 0.0325
-7.000 -0.2842 0.01208 0.00597 -0.0921 0.7263 0.0329
-6.750 -0.2560 0.01184 0.00567 -0.0921 0.7185 0.0334
-6.500 -0.2278 0.01160 0.00536 -0.0921 0.7104 0.0338
-6.250 -0.2006 0.01117 0.00488 -0.0920 0.7030 0.0346
-6.000 -0.1724 0.01088 0.00456 -0.0920 0.6952 0.0353
-5.750 -0.1442 0.01068 0.00430 -0.0920 0.6874 0.0360
-5.500 -0.1155 0.01047 0.00406 -0.0920 0.6800 0.0368
-5.250 -0.0870 0.01031 0.00384 -0.0921 0.6723 0.0376
-5.000 -0.0582 0.01013 0.00362 -0.0921 0.6657 0.0385
-4.750 -0.0297 0.00990 0.00338 -0.0922 0.6590 0.0402
-4.500 -0.0011 0.00976 0.00320 -0.0923 0.6524 0.0419
-4.250 0.0280 0.00959 0.00302 -0.0924 0.6466 0.0445
-4.000 0.0567 0.00943 0.00286 -0.0925 0.6400 0.0493
-3.750 0.0853 0.00927 0.00274 -0.0926 0.6337 0.0611
-3.500 0.1144 0.00915 0.00267 -0.0928 0.6276 0.0724
-3.250 0.1435 0.00911 0.00261 -0.0929 0.6212 0.0789
-3.000 0.1725 0.00904 0.00255 -0.0931 0.6155 0.0849
-2.750 0.2020 0.00901 0.00250 -0.0933 0.6096 0.0885
-2.500 0.2309 0.00893 0.00242 -0.0934 0.6033 0.0939
-2.250 0.2601 0.00889 0.00237 -0.0936 0.5972 0.0982
-2.000 0.2893 0.00883 0.00231 -0.0938 0.5905 0.1031
-1.750 0.3181 0.00880 0.00226 -0.0939 0.5831 0.1089
-1.500 0.3474 0.00874 0.00220 -0.0942 0.5767 0.1150
-1.250 0.3763 0.00868 0.00216 -0.0943 0.5692 0.1247
-1.000 0.4051 0.00862 0.00213 -0.0945 0.5619 0.1402
-0.750 0.4338 0.00850 0.00210 -0.0947 0.5534 0.1731
-0.500 0.4621 0.00839 0.00209 -0.0948 0.5446 0.2152
-0.250 0.4904 0.00827 0.00209 -0.0950 0.5347 0.2647
0.250 0.5463 0.00802 0.00214 -0.0953 0.5146 0.3932
0.500 0.5739 0.00782 0.00217 -0.0954 0.5043 0.4900
0.750 0.6003 0.00758 0.00224 -0.0953 0.4939 0.6156
1.000 0.6257 0.00730 0.00233 -0.0948 0.4840 0.7529
1.250 0.6492 0.00714 0.00245 -0.0937 0.4757 0.8611
1.500 0.6723 0.00713 0.00256 -0.0923 0.4677 0.9280
1.750 0.7016 0.00724 0.00264 -0.0925 0.4601 0.9658
2.000 0.7385 0.00736 0.00272 -0.0944 0.4531 0.9844
2.250 0.7796 0.00755 0.00282 -0.0974 0.4456 0.9959
2.500 0.8177 0.00765 0.00290 -0.0996 0.4400 1.0000
2.750 0.8424 0.00778 0.00297 -0.0991 0.4340 1.0000
3.000 0.8668 0.00793 0.00307 -0.0984 0.4278 1.0000
3.250 0.8928 0.00802 0.00314 -0.0981 0.4228 1.0000
3.500 0.9184 0.00816 0.00323 -0.0977 0.4169 1.0000
3.750 0.9437 0.00834 0.00335 -0.0973 0.4111 1.0000
4.000 0.9708 0.00842 0.00343 -0.0972 0.4079 1.0000
4.250 0.9977 0.00854 0.00353 -0.0971 0.4043 1.0000
4.500 1.0242 0.00868 0.00365 -0.0969 0.4004 1.0000
4.750 1.0501 0.00886 0.00379 -0.0967 0.3962 1.0000
5.000 1.0769 0.00899 0.00392 -0.0966 0.3930 1.0000
5.250 1.1042 0.00909 0.00403 -0.0966 0.3897 1.0000
5.500 1.1309 0.00923 0.00415 -0.0965 0.3857 1.0000
5.750 1.1569 0.00941 0.00430 -0.0963 0.3815 1.0000
6.000 1.1825 0.00961 0.00448 -0.0960 0.3772 1.0000
6.250 1.2097 0.00971 0.00460 -0.0961 0.3744 1.0000
6.500 1.2363 0.00984 0.00475 -0.0960 0.3706 1.0000
6.750 1.2619 0.01002 0.00491 -0.0958 0.3662 1.0000
7.000 1.2864 0.01026 0.00511 -0.0954 0.3607 1.0000
7.250 1.3131 0.01037 0.00525 -0.0953 0.3562 1.0000
7.500 1.3384 0.01055 0.00543 -0.0951 0.3513 1.0000
7.750 1.3623 0.01079 0.00565 -0.0946 0.3462 1.0000
8.000 1.3875 0.01096 0.00584 -0.0943 0.3420 1.0000
8.250 1.4122 0.01115 0.00603 -0.0940 0.3366 1.0000
8.500 1.4343 0.01144 0.00629 -0.0932 0.3297 1.0000
8.750 1.4581 0.01164 0.00650 -0.0927 0.3229 1.0000
9.000 1.4789 0.01195 0.00678 -0.0918 0.3149 1.0000
9.250 1.4996 0.01221 0.00705 -0.0908 0.3084 1.0000
9.500 1.5177 0.01255 0.00737 -0.0893 0.3003 1.0000
9.750 1.5364 0.01291 0.00772 -0.0880 0.2926 1.0000
10.000 1.5528 0.01338 0.00817 -0.0864 0.2832 1.0000
10.250 1.5703 0.01384 0.00861 -0.0851 0.2735 1.0000
10.500 1.5850 0.01445 0.00917 -0.0834 0.2618 1.0000
10.750 1.5978 0.01518 0.00985 -0.0816 0.2488 1.0000
11.000 1.6097 0.01601 0.01062 -0.0798 0.2362 1.0000
11.250 1.6234 0.01676 0.01134 -0.0783 0.2263 1.0000
11.500 1.6362 0.01760 0.01216 -0.0767 0.2172 1.0000
12.000 1.6606 0.01944 0.01398 -0.0738 0.2010 1.0000
12.250 1.6703 0.02057 0.01508 -0.0723 0.1935 1.0000
12.500 1.6840 0.02147 0.01601 -0.0712 0.1883 1.0000
12.750 1.6936 0.02267 0.01720 -0.0698 0.1820 1.0000
13.000 1.7042 0.02383 0.01838 -0.0686 0.1765 1.0000
13.250 1.7150 0.02501 0.01957 -0.0674 0.1712 1.0000
13.500 1.7218 0.02651 0.02107 -0.0660 0.1658 1.0000
13.750 1.7325 0.02774 0.02235 -0.0650 0.1615 1.0000
14.000 1.7396 0.02926 0.02389 -0.0639 0.1561 1.0000
14.250 1.7445 0.03102 0.02565 -0.0626 0.1507 1.0000
14.500 1.7524 0.03255 0.02722 -0.0617 0.1452 1.0000
14.750 1.7528 0.03477 0.02943 -0.0604 0.1381 1.0000
15.000 1.7576 0.03669 0.03137 -0.0594 0.1314 1.0000
15.250 1.7570 0.03916 0.03384 -0.0584 0.1241 1.0000
15.500 1.7538 0.04192 0.03659 -0.0573 0.1152 1.0000
15.750 1.7490 0.04494 0.03960 -0.0564 0.1061 1.0000
16.000 1.7423 0.04824 0.04290 -0.0555 0.0986 1.0000
16.250 1.7340 0.05175 0.04642 -0.0547 0.0925 1.0000
16.500 1.7292 0.05500 0.04971 -0.0542 0.0883 1.0000
16.750 1.7213 0.05864 0.05339 -0.0537 0.0844 1.0000
17.000 1.7173 0.06192 0.05673 -0.0534 0.0814 1.0000
17.250 1.7117 0.06541 0.06027 -0.0531 0.0786 1.0000
17.500 1.7035 0.06926 0.06417 -0.0530 0.0758 1.0000
17.750 1.6981 0.07284 0.06782 -0.0530 0.0732 1.0000
18.000 1.6944 0.07627 0.07131 -0.0530 0.0706 1.0000
18.250 1.6858 0.08031 0.07540 -0.0532 0.0679 1.0000
18.500 1.6767 0.08449 0.07964 -0.0535 0.0652 1.0000
18.750 1.6716 0.08820 0.08341 -0.0538 0.0622 1.0000
19.000 1.6605 0.09273 0.08797 -0.0543 0.0585 1.0000
19.250 1.6526 0.09683 0.09212 -0.0549 0.0544 1.0000
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