GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.85 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe07k-il-1000000-n5.txt Download as CSV file: xf-goe07k-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1193 0.08321 0.08130 -0.1314 0.9467 0.0042
-10.000 -0.1297 0.07476 0.07286 -0.1362 0.9428 0.0039
-9.750 -0.3358 0.02302 0.01989 -0.1624 0.9108 0.0037
-9.500 -0.3282 0.02002 0.01648 -0.1606 0.9064 0.0038
-9.250 -0.3102 0.01792 0.01403 -0.1602 0.9035 0.0040
-9.000 -0.2877 0.01665 0.01253 -0.1603 0.9011 0.0041
-8.750 -0.2801 0.01582 0.01155 -0.1566 0.8971 0.0042
-8.500 -0.2626 0.01502 0.01059 -0.1550 0.8939 0.0043
-8.250 -0.2401 0.01429 0.00971 -0.1545 0.8913 0.0044
-8.000 -0.2124 0.01375 0.00906 -0.1551 0.8891 0.0048
-7.750 -0.1849 0.01290 0.00802 -0.1557 0.8872 0.0049
-7.500 -0.1744 0.01247 0.00748 -0.1522 0.8839 0.0050
-7.250 -0.1585 0.01197 0.00687 -0.1498 0.8808 0.0053
-7.000 -0.1377 0.01147 0.00624 -0.1486 0.8782 0.0054
-6.750 -0.1140 0.01095 0.00562 -0.1481 0.8759 0.0058
-6.500 -0.0866 0.01051 0.00509 -0.1484 0.8738 0.0061
-6.250 -0.0639 0.01023 0.00475 -0.1476 0.8715 0.0064
-6.000 -0.0506 0.00994 0.00441 -0.1445 0.8680 0.0068
-5.750 -0.0306 0.00972 0.00413 -0.1430 0.8651 0.0074
-5.500 -0.0082 0.00939 0.00374 -0.1420 0.8626 0.0078
-5.250 0.0174 0.00913 0.00343 -0.1418 0.8603 0.0087
-5.000 0.0460 0.00890 0.00314 -0.1422 0.8584 0.0096
-4.750 0.0602 0.00869 0.00290 -0.1393 0.8553 0.0105
-4.500 0.0782 0.00850 0.00270 -0.1373 0.8521 0.0117
-4.250 0.1001 0.00833 0.00249 -0.1361 0.8491 0.0129
-4.000 0.1241 0.00813 0.00227 -0.1355 0.8465 0.0155
-3.750 0.1512 0.00797 0.00208 -0.1356 0.8441 0.0197
-3.500 0.1675 0.00783 0.00196 -0.1331 0.8407 0.0238
-3.250 0.1872 0.00772 0.00189 -0.1314 0.8374 0.0323
-3.000 0.2097 0.00764 0.00180 -0.1304 0.8343 0.0379
-2.750 0.2349 0.00757 0.00173 -0.1300 0.8317 0.0435
-2.500 0.2613 0.00754 0.00166 -0.1299 0.8292 0.0465
-2.250 0.2801 0.00752 0.00164 -0.1280 0.8258 0.0477
-2.000 0.3004 0.00743 0.00153 -0.1265 0.8222 0.0509
-1.750 0.3232 0.00735 0.00144 -0.1255 0.8189 0.0533
-1.500 0.3485 0.00729 0.00136 -0.1251 0.8160 0.0552
-1.250 0.3694 0.00725 0.00131 -0.1237 0.8125 0.0565
-1.000 0.3903 0.00722 0.00127 -0.1223 0.8087 0.0575
-0.750 0.4132 0.00719 0.00122 -0.1213 0.8053 0.0581
-0.500 0.4377 0.00717 0.00118 -0.1208 0.8022 0.0594
-0.250 0.4612 0.00715 0.00115 -0.1200 0.7992 0.0608
0.000 0.4819 0.00712 0.00116 -0.1185 0.7955 0.0679
0.250 0.5006 0.00698 0.00118 -0.1166 0.7909 0.1328
0.500 0.5201 0.00675 0.00121 -0.1151 0.7863 0.2447
0.750 0.5323 0.00645 0.00130 -0.1118 0.7799 0.3937
1.000 0.5485 0.00622 0.00135 -0.1095 0.7737 0.5128
1.250 0.5631 0.00591 0.00144 -0.1068 0.7688 0.6577
1.750 0.7917 0.00591 0.00227 -0.1484 0.7538 0.9907
2.000 0.8253 0.00604 0.00237 -0.1500 0.7453 0.9942
2.250 0.8565 0.00615 0.00244 -0.1511 0.7328 0.9966
2.500 0.8917 0.00625 0.00251 -0.1532 0.7213 0.9991
2.750 0.9128 0.00639 0.00260 -0.1519 0.7056 1.0000
3.000 0.9250 0.00652 0.00271 -0.1485 0.6933 1.0000
3.250 0.9356 0.00667 0.00282 -0.1448 0.6775 1.0000
3.500 0.9399 0.00694 0.00299 -0.1397 0.6499 1.0000
3.750 0.9368 0.00736 0.00324 -0.1329 0.6062 1.0000
4.000 0.9199 0.00821 0.00372 -0.1233 0.5311 1.0000
4.250 0.9131 0.00902 0.00422 -0.1161 0.4656 1.0000
4.500 0.9058 0.00997 0.00478 -0.1091 0.3845 1.0000
4.750 0.9013 0.01097 0.00538 -0.1028 0.2967 1.0000
5.000 0.9003 0.01192 0.00598 -0.0974 0.2210 1.0000
5.250 0.9112 0.01248 0.00638 -0.0944 0.1853 1.0000
5.500 0.9196 0.01319 0.00686 -0.0909 0.1338 1.0000
5.750 0.9253 0.01405 0.00745 -0.0871 0.0763 1.0000
6.000 0.9416 0.01446 0.00782 -0.0852 0.0641 1.0000
6.250 0.9572 0.01490 0.00822 -0.0832 0.0500 1.0000
6.500 0.9698 0.01551 0.00870 -0.0807 0.0263 1.0000
6.750 0.9854 0.01599 0.00915 -0.0788 0.0180 1.0000
7.000 1.0016 0.01645 0.00960 -0.0770 0.0139 1.0000
7.250 1.0180 0.01689 0.01005 -0.0752 0.0114 1.0000
7.500 1.0343 0.01736 0.01053 -0.0735 0.0095 1.0000
7.750 1.0505 0.01784 0.01103 -0.0717 0.0085 1.0000
8.000 1.0669 0.01832 0.01154 -0.0701 0.0077 1.0000
8.250 1.0829 0.01882 0.01208 -0.0684 0.0069 1.0000
8.500 1.0975 0.01942 0.01270 -0.0665 0.0061 1.0000
8.750 1.1138 0.01993 0.01326 -0.0649 0.0057 1.0000
9.000 1.1292 0.02049 0.01386 -0.0631 0.0052 1.0000
9.250 1.1439 0.02111 0.01452 -0.0613 0.0049 1.0000
9.500 1.1575 0.02179 0.01523 -0.0594 0.0045 1.0000
9.750 1.1728 0.02239 0.01588 -0.0578 0.0041 1.0000
10.000 1.1859 0.02315 0.01670 -0.0558 0.0040 1.0000
10.250 1.1999 0.02383 0.01745 -0.0541 0.0037 1.0000
10.500 1.2134 0.02457 0.01824 -0.0523 0.0036 1.0000
10.750 1.2254 0.02542 0.01914 -0.0503 0.0034 1.0000
11.000 1.2378 0.02624 0.02001 -0.0485 0.0032 1.0000
11.250 1.2462 0.02740 0.02124 -0.0460 0.0031 1.0000
11.500 1.2587 0.02824 0.02217 -0.0443 0.0030 1.0000
11.750 1.2702 0.02916 0.02316 -0.0425 0.0029 1.0000
12.000 1.2814 0.03012 0.02421 -0.0406 0.0028 1.0000
12.250 1.2907 0.03123 0.02542 -0.0386 0.0027 1.0000
12.500 1.2987 0.03249 0.02678 -0.0365 0.0027 1.0000
12.750 1.3096 0.03351 0.02787 -0.0348 0.0025 1.0000
13.000 1.3182 0.03472 0.02917 -0.0329 0.0025 1.0000
13.250 1.3277 0.03588 0.03040 -0.0312 0.0024 1.0000
13.500 1.3382 0.03694 0.03152 -0.0297 0.0022 1.0000
13.750 1.3444 0.03842 0.03309 -0.0278 0.0022 1.0000
14.000 1.3494 0.04003 0.03481 -0.0258 0.0021 1.0000
14.250 1.3490 0.04217 0.03709 -0.0234 0.0021 1.0000
14.500 1.3531 0.04391 0.03894 -0.0216 0.0020 1.0000
14.750 1.3530 0.04610 0.04129 -0.0195 0.0020 1.0000
15.000 1.3562 0.04801 0.04331 -0.0179 0.0020 1.0000
15.250 1.3586 0.05006 0.04550 -0.0163 0.0019 1.0000
15.500 1.3546 0.05283 0.04844 -0.0144 0.0019 1.0000
15.750 1.3509 0.05562 0.05140 -0.0128 0.0019 1.0000
16.000 1.3474 0.05850 0.05444 -0.0115 0.0019 1.0000
16.250 1.3471 0.06108 0.05716 -0.0105 0.0018 1.0000
16.500 1.3329 0.06546 0.06174 -0.0092 0.0018 1.0000
16.750 1.3250 0.06918 0.06563 -0.0085 0.0018 1.0000
17.000 1.3122 0.07373 0.07034 -0.0081 0.0018 1.0000
17.250 1.3029 0.07801 0.07478 -0.0082 0.0017 1.0000
17.500 1.2991 0.08169 0.07857 -0.0087 0.0017 1.0000
17.750 1.2719 0.08920 0.08631 -0.0100 0.0017 1.0000
18.000 1.2575 0.09501 0.09228 -0.0117 0.0017 1.0000
18.250 1.2542 0.09915 0.09651 -0.0132 0.0016 1.0000
18.500 1.2275 0.10774 0.10529 -0.0165 0.0017 1.0000
18.750 1.1896 0.11925 0.11703 -0.0219 0.0017 1.0000
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