GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.64 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe682-il-1000000-n5.txt Download as CSV file: xf-goe682-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0685 0.03329 0.03067 -0.0951 1.0000 0.0118
-14.500 -1.0787 0.03017 0.02737 -0.0935 1.0000 0.0120
-14.250 -1.0642 0.02770 0.02474 -0.0948 0.9986 0.0125
-14.000 -1.0417 0.02581 0.02269 -0.0966 0.9964 0.0132
-13.750 -1.0170 0.02426 0.02100 -0.0981 0.9943 0.0137
-13.500 -0.9931 0.02296 0.01957 -0.0990 0.9914 0.0143
-13.250 -0.9653 0.02196 0.01851 -0.1002 0.9885 0.0150
-13.000 -0.9354 0.02112 0.01759 -0.1016 0.9862 0.0157
-12.750 -0.9065 0.02036 0.01675 -0.1026 0.9837 0.0165
-12.500 -0.8807 0.01964 0.01593 -0.1029 0.9800 0.0171
-12.250 -0.8525 0.01890 0.01508 -0.1037 0.9775 0.0176
-12.000 -0.8224 0.01821 0.01433 -0.1049 0.9757 0.0182
-11.750 -0.7935 0.01772 0.01381 -0.1055 0.9725 0.0187
-11.500 -0.7645 0.01730 0.01334 -0.1061 0.9687 0.0192
-11.250 -0.7335 0.01685 0.01283 -0.1071 0.9657 0.0197
-11.000 -0.7037 0.01643 0.01235 -0.1078 0.9621 0.0203
-10.750 -0.6748 0.01600 0.01185 -0.1083 0.9569 0.0209
-10.500 -0.6440 0.01555 0.01130 -0.1092 0.9525 0.0213
-10.250 -0.6166 0.01514 0.01080 -0.1093 0.9453 0.0216
-10.000 -0.5878 0.01474 0.01031 -0.1097 0.9389 0.0218
-9.750 -0.5628 0.01409 0.00957 -0.1095 0.9306 0.0225
-9.500 -0.5361 0.01372 0.00914 -0.1094 0.9226 0.0230
-9.250 -0.5094 0.01343 0.00879 -0.1092 0.9136 0.0234
-9.000 -0.4830 0.01319 0.00849 -0.1089 0.9042 0.0239
-8.750 -0.4567 0.01294 0.00817 -0.1086 0.8950 0.0244
-8.500 -0.4308 0.01267 0.00782 -0.1082 0.8853 0.0249
-8.250 -0.4050 0.01235 0.00742 -0.1078 0.8762 0.0253
-8.000 -0.3794 0.01206 0.00702 -0.1074 0.8661 0.0257
-7.750 -0.3535 0.01179 0.00666 -0.1069 0.8560 0.0261
-7.500 -0.3277 0.01151 0.00629 -0.1065 0.8459 0.0264
-7.250 -0.3019 0.01125 0.00593 -0.1060 0.8359 0.0266
-7.000 -0.2758 0.01100 0.00560 -0.1056 0.8267 0.0267
-6.750 -0.2507 0.01062 0.00512 -0.1050 0.8156 0.0271
-6.500 -0.2256 0.01027 0.00467 -0.1045 0.8028 0.0278
-6.250 -0.1999 0.01003 0.00436 -0.1039 0.7889 0.0284
-6.000 -0.1740 0.00983 0.00408 -0.1035 0.7752 0.0288
-5.750 -0.1480 0.00966 0.00383 -0.1030 0.7611 0.0292
-5.500 -0.1219 0.00950 0.00359 -0.1025 0.7469 0.0296
-5.250 -0.0957 0.00936 0.00337 -0.1020 0.7345 0.0301
-5.000 -0.0692 0.00921 0.00315 -0.1017 0.7235 0.0306
-4.750 -0.0424 0.00906 0.00295 -0.1013 0.7139 0.0311
-4.500 -0.0157 0.00893 0.00276 -0.1010 0.7046 0.0316
-4.250 0.0112 0.00881 0.00258 -0.1006 0.6946 0.0321
-4.000 0.0382 0.00871 0.00242 -0.1003 0.6854 0.0325
-3.750 0.0649 0.00860 0.00225 -0.1000 0.6762 0.0331
-3.500 0.0920 0.00845 0.00208 -0.0997 0.6687 0.0347
-3.250 0.1190 0.00836 0.00197 -0.0994 0.6604 0.0361
-3.000 0.1462 0.00828 0.00186 -0.0991 0.6529 0.0373
-2.750 0.1733 0.00822 0.00175 -0.0989 0.6446 0.0387
-2.500 0.2007 0.00816 0.00166 -0.0986 0.6375 0.0398
-2.250 0.2277 0.00808 0.00157 -0.0983 0.6297 0.0428
-2.000 0.2548 0.00803 0.00150 -0.0981 0.6201 0.0460
-1.750 0.2816 0.00802 0.00145 -0.0977 0.6095 0.0486
-1.500 0.3087 0.00796 0.00139 -0.0975 0.5996 0.0535
-1.250 0.3357 0.00793 0.00135 -0.0972 0.5904 0.0582
-1.000 0.3625 0.00792 0.00131 -0.0968 0.5795 0.0646
-0.750 0.3896 0.00788 0.00127 -0.0966 0.5690 0.0722
-0.500 0.4163 0.00785 0.00124 -0.0963 0.5582 0.0842
-0.250 0.4424 0.00778 0.00122 -0.0959 0.5447 0.1164
0.000 0.4683 0.00775 0.00124 -0.0954 0.5268 0.1532
0.250 0.4942 0.00780 0.00126 -0.0950 0.5057 0.1757
0.500 0.5200 0.00785 0.00130 -0.0945 0.4870 0.1973
0.750 0.5461 0.00790 0.00134 -0.0941 0.4722 0.2167
1.000 0.5722 0.00794 0.00139 -0.0937 0.4582 0.2408
1.250 0.5981 0.00799 0.00145 -0.0933 0.4442 0.2672
1.500 0.6240 0.00803 0.00151 -0.0929 0.4311 0.2959
1.750 0.6495 0.00800 0.00159 -0.0925 0.4208 0.3568
2.000 0.6722 0.00758 0.00171 -0.0916 0.4119 0.5824
2.250 0.6864 0.00689 0.00187 -0.0886 0.4042 0.8841
2.500 0.7521 0.00697 0.00200 -0.0970 0.3907 0.9942
2.750 0.7802 0.00711 0.00209 -0.0970 0.3805 1.0000
3.000 0.8046 0.00726 0.00218 -0.0963 0.3691 1.0000
3.250 0.8289 0.00743 0.00228 -0.0955 0.3565 1.0000
3.500 0.8533 0.00760 0.00239 -0.0948 0.3433 1.0000
3.750 0.8775 0.00779 0.00250 -0.0940 0.3285 1.0000
4.000 0.9012 0.00801 0.00264 -0.0932 0.3112 1.0000
4.250 0.9246 0.00826 0.00280 -0.0923 0.2917 1.0000
4.500 0.9476 0.00854 0.00297 -0.0914 0.2722 1.0000
4.750 0.9706 0.00881 0.00317 -0.0905 0.2553 1.0000
5.000 0.9936 0.00910 0.00337 -0.0896 0.2398 1.0000
5.250 1.0174 0.00932 0.00355 -0.0888 0.2307 1.0000
5.500 1.0414 0.00953 0.00372 -0.0881 0.2235 1.0000
5.750 1.0655 0.00973 0.00391 -0.0874 0.2178 1.0000
6.000 1.0893 0.00994 0.00410 -0.0866 0.2105 1.0000
6.250 1.1126 0.01019 0.00431 -0.0858 0.2025 1.0000
6.500 1.1363 0.01040 0.00451 -0.0851 0.1962 1.0000
6.750 1.1592 0.01066 0.00474 -0.0842 0.1889 1.0000
7.000 1.1830 0.01085 0.00494 -0.0835 0.1843 1.0000
7.250 1.2052 0.01114 0.00518 -0.0825 0.1756 1.0000
7.500 1.2281 0.01137 0.00541 -0.0816 0.1682 1.0000
7.750 1.2496 0.01168 0.00568 -0.0806 0.1586 1.0000
8.000 1.2695 0.01207 0.00598 -0.0793 0.1432 1.0000
8.250 1.2862 0.01263 0.00640 -0.0774 0.1197 1.0000
8.500 1.2987 0.01340 0.00699 -0.0749 0.0900 1.0000
8.750 1.3110 0.01406 0.00755 -0.0723 0.0725 1.0000
9.000 1.3232 0.01465 0.00806 -0.0697 0.0582 1.0000
9.250 1.3311 0.01545 0.00874 -0.0664 0.0382 1.0000
9.500 1.3386 0.01631 0.00950 -0.0631 0.0220 1.0000
9.750 1.3514 0.01692 0.01009 -0.0608 0.0170 1.0000
10.000 1.3659 0.01745 0.01064 -0.0589 0.0152 1.0000
10.250 1.3797 0.01804 0.01125 -0.0569 0.0135 1.0000
10.500 1.3945 0.01857 0.01182 -0.0551 0.0128 1.0000
10.750 1.4082 0.01918 0.01246 -0.0532 0.0118 1.0000
11.000 1.4210 0.01987 0.01317 -0.0513 0.0112 1.0000
11.250 1.4328 0.02063 0.01398 -0.0493 0.0103 1.0000
11.500 1.4461 0.02132 0.01471 -0.0477 0.0099 1.0000
11.750 1.4584 0.02210 0.01554 -0.0460 0.0096 1.0000
12.000 1.4700 0.02295 0.01644 -0.0443 0.0091 1.0000
12.250 1.4808 0.02388 0.01741 -0.0427 0.0088 1.0000
12.500 1.4906 0.02492 0.01850 -0.0410 0.0084 1.0000
12.750 1.4990 0.02610 0.01973 -0.0394 0.0080 1.0000
13.000 1.5063 0.02742 0.02111 -0.0378 0.0077 1.0000
13.250 1.5159 0.02860 0.02235 -0.0365 0.0075 1.0000
13.500 1.5242 0.02993 0.02374 -0.0353 0.0073 1.0000
13.750 1.5319 0.03136 0.02523 -0.0341 0.0071 1.0000
14.000 1.5382 0.03295 0.02689 -0.0330 0.0069 1.0000
14.250 1.5439 0.03466 0.02867 -0.0320 0.0067 1.0000
14.500 1.5491 0.03647 0.03054 -0.0311 0.0064 1.0000
14.750 1.5526 0.03851 0.03265 -0.0303 0.0062 1.0000
15.000 1.5549 0.04072 0.03494 -0.0296 0.0061 1.0000
15.250 1.5553 0.04322 0.03751 -0.0290 0.0059 1.0000
15.500 1.5537 0.04605 0.04043 -0.0286 0.0058 1.0000
15.750 1.5521 0.04897 0.04344 -0.0284 0.0057 1.0000
16.000 1.5521 0.05177 0.04633 -0.0283 0.0056 1.0000
16.250 1.5509 0.05483 0.04947 -0.0284 0.0055 1.0000
16.500 1.5479 0.05819 0.05293 -0.0286 0.0055 1.0000
16.750 1.5439 0.06177 0.05662 -0.0291 0.0054 1.0000
17.000 1.5384 0.06565 0.06060 -0.0297 0.0053 1.0000
17.250 1.5327 0.06969 0.06474 -0.0305 0.0052 1.0000
17.500 1.5258 0.07403 0.06918 -0.0316 0.0052 1.0000
17.750 1.5188 0.07845 0.07370 -0.0328 0.0051 1.0000
18.000 1.5073 0.08371 0.07908 -0.0344 0.0051 1.0000
18.250 1.4980 0.08874 0.08422 -0.0361 0.0050 1.0000
18.500 1.4857 0.09436 0.08995 -0.0381 0.0050 1.0000
18.750 1.4765 0.09954 0.09523 -0.0401 0.0049 1.0000
19.000 1.4609 0.10597 0.10179 -0.0427 0.0049 1.0000
19.250 1.4497 0.11174 0.10766 -0.0452 0.0049 1.0000
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