GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 100,000 Max Cl/Cd: 47.35 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe481a-il-100000.txt Download as CSV file: xf-goe481a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 481A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.250 -0.2568 0.10746 0.10276 -0.0334 0.9704 0.1403
-6.000 -0.2888 0.10589 0.10120 -0.0400 0.9521 0.1441
-5.750 -0.2791 0.10111 0.09641 -0.0455 0.9416 0.1456
-5.500 -0.2468 0.09757 0.09289 -0.0448 0.9348 0.1471
-5.250 -0.2248 0.09449 0.08980 -0.0462 0.9256 0.1495
-5.000 -0.2026 0.09080 0.08608 -0.0513 0.9175 0.1539
-4.750 -0.2029 0.08537 0.08046 -0.0631 0.9018 0.1595
-4.500 -0.1881 0.08254 0.07769 -0.0608 0.8902 0.1606
-4.250 -0.1529 0.07940 0.07457 -0.0623 0.8861 0.1642
-4.000 -0.1411 0.07635 0.07140 -0.0662 0.8716 0.1719
-3.750 -0.1314 0.07228 0.06720 -0.0689 0.8585 0.1757
-3.500 -0.0989 0.06907 0.06402 -0.0700 0.8536 0.1785
-3.250 -0.0851 0.06686 0.06179 -0.0696 0.8410 0.1826
-3.000 -0.0517 0.06239 0.05705 -0.0759 0.8353 0.1930
-2.750 -0.0400 0.06047 0.05517 -0.0738 0.8222 0.1955
-2.500 -0.0035 0.05712 0.05155 -0.0783 0.8175 0.2106
-2.250 0.0081 0.05534 0.04986 -0.0758 0.8047 0.2138
-2.000 0.0442 0.05239 0.04672 -0.0787 0.8001 0.2307
-1.750 0.0623 0.04313 0.03583 -0.0804 0.7886 0.1452
-1.500 0.0976 0.04037 0.03274 -0.0814 0.7835 0.1443
-1.250 0.1382 0.03741 0.02935 -0.0828 0.7807 0.1445
-0.750 0.1940 0.03380 0.02550 -0.0820 0.7644 0.1476
-0.500 0.2427 0.03167 0.02320 -0.0847 0.7619 0.1527
-0.250 0.2582 0.03112 0.02236 -0.0820 0.7491 0.1567
0.000 0.3072 0.02895 0.02001 -0.0848 0.7454 0.1625
0.250 0.3669 0.02707 0.01781 -0.0893 0.7424 0.1741
0.500 0.3835 0.02658 0.01741 -0.0872 0.7295 0.1813
0.750 0.4469 0.02470 0.01541 -0.0928 0.7247 0.1991
1.000 0.4738 0.02423 0.01488 -0.0922 0.7133 0.2128
1.250 0.5353 0.02298 0.01361 -0.0980 0.7057 0.2348
1.500 0.5632 0.02280 0.01337 -0.0977 0.6943 0.2496
1.750 0.6283 0.02195 0.01254 -0.1046 0.6850 0.2736
2.000 0.6459 0.02207 0.01266 -0.1023 0.6728 0.2864
2.250 0.7248 0.02145 0.01204 -0.1121 0.6632 0.3119
2.500 0.7307 0.02171 0.01240 -0.1077 0.6511 0.3238
2.750 0.7916 0.02145 0.01223 -0.1141 0.6409 0.3635
3.000 0.9565 0.02063 0.01254 -0.1420 0.6236 1.0000
3.250 0.9617 0.02115 0.01302 -0.1374 0.6130 1.0000
3.500 1.0046 0.02143 0.01302 -0.1401 0.6030 1.0000
3.750 1.0062 0.02195 0.01355 -0.1348 0.5924 1.0000
4.000 1.0500 0.02220 0.01351 -0.1376 0.5819 1.0000
4.250 1.0473 0.02273 0.01410 -0.1315 0.5718 1.0000
4.500 1.0885 0.02299 0.01411 -0.1339 0.5620 1.0000
4.750 1.0868 0.02352 0.01472 -0.1280 0.5524 1.0000
5.000 1.1205 0.02378 0.01480 -0.1289 0.5430 1.0000
5.250 1.1257 0.02431 0.01535 -0.1244 0.5338 1.0000
5.500 1.1494 0.02461 0.01556 -0.1234 0.5248 1.0000
5.750 1.1668 0.02508 0.01598 -0.1213 0.5164 1.0000
6.000 1.1777 0.02553 0.01643 -0.1179 0.5079 1.0000
6.250 1.2175 0.02584 0.01656 -0.1201 0.5002 1.0000
6.500 1.2120 0.02646 0.01732 -0.1137 0.4924 1.0000
6.750 1.2359 0.02680 0.01758 -0.1128 0.4847 1.0000
7.000 1.2567 0.02730 0.01805 -0.1115 0.4775 1.0000
7.250 1.2590 0.02789 0.01873 -0.1066 0.4699 1.0000
7.500 1.2948 0.02812 0.01881 -0.1080 0.4626 1.0000
7.750 1.2947 0.02880 0.01959 -0.1028 0.4555 1.0000
8.000 1.3029 0.02923 0.02005 -0.0991 0.4479 1.0000
8.250 1.3405 0.02949 0.02017 -0.1008 0.4401 1.0000
8.500 1.3264 0.03016 0.02100 -0.0931 0.4327 1.0000
8.750 1.3548 0.03033 0.02106 -0.0930 0.4247 1.0000
9.000 1.3579 0.03096 0.02176 -0.0886 0.4171 1.0000
9.250 1.3646 0.03145 0.02229 -0.0849 0.4090 1.0000
9.500 1.3939 0.03173 0.02245 -0.0851 0.4009 1.0000
9.750 1.3841 0.03255 0.02343 -0.0787 0.3928 1.0000
10.000 1.4251 0.03252 0.02318 -0.0807 0.3836 1.0000
10.250 1.4050 0.03357 0.02445 -0.0729 0.3755 1.0000
10.500 1.4466 0.03342 0.02402 -0.0749 0.3654 1.0000
10.750 1.4234 0.03465 0.02551 -0.0669 0.3574 1.0000
11.000 1.4607 0.03450 0.02508 -0.0682 0.3472 1.0000
11.250 1.4389 0.03589 0.02673 -0.0608 0.3395 1.0000
11.500 1.4653 0.03602 0.02669 -0.0605 0.3303 1.0000
11.750 1.4552 0.03736 0.02818 -0.0553 0.3227 1.0000
12.000 1.4671 0.03793 0.02870 -0.0531 0.3145 1.0000
12.250 1.4751 0.03888 0.02965 -0.0506 0.3073 1.0000
12.500 1.4695 0.04026 0.03117 -0.0466 0.3004 1.0000
12.750 1.5088 0.04022 0.03087 -0.0480 0.2928 1.0000
13.000 1.4846 0.04241 0.03336 -0.0420 0.2877 1.0000
13.250 1.4849 0.04371 0.03474 -0.0391 0.2815 1.0000
13.500 1.5185 0.04377 0.03461 -0.0397 0.2749 1.0000
13.750 1.4927 0.04638 0.03752 -0.0345 0.2703 1.0000
14.000 1.4898 0.04805 0.03928 -0.0317 0.2647 1.0000
14.250 1.5285 0.04766 0.03866 -0.0326 0.2581 1.0000
14.500 1.4969 0.05100 0.04232 -0.0278 0.2541 1.0000
14.750 1.4839 0.05352 0.04501 -0.0249 0.2491 1.0000
15.000 1.5340 0.05214 0.04331 -0.0262 0.2419 1.0000
15.250 1.4942 0.05651 0.04805 -0.0219 0.2384 1.0000
15.500 1.4677 0.06048 0.05223 -0.0194 0.2338 1.0000
15.750 1.5297 0.05768 0.04905 -0.0204 0.2259 1.0000
16.000 1.4802 0.06353 0.05530 -0.0172 0.2227 1.0000
16.250 1.4392 0.06959 0.06165 -0.0156 0.2185 1.0000
16.500 1.5189 0.06454 0.05614 -0.0158 0.2102 1.0000
16.750 1.4568 0.07252 0.06454 -0.0141 0.2074 1.0000
17.000 1.3579 0.08657 0.07908 -0.0153 0.2042 1.0000
17.250 1.4547 0.07754 0.06965 -0.0128 0.1969 1.0000
17.500 1.4234 0.08380 0.07609 -0.0130 0.1931 1.0000
17.750 0.8715 0.19990 0.19306 -0.0651 0.2253 1.0000
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Polar data table (+)
Polar graphs
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