GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 100,000 Max Cl/Cd: 57.12 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe442-il-100000-n5.txt Download as CSV file: xf-goe442-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3491 0.10602 0.10117 -0.0288 1.0000 0.0404
-8.250 -0.3520 0.10370 0.09893 -0.0287 1.0000 0.0405
-8.000 -0.3564 0.10143 0.09675 -0.0283 1.0000 0.0405
-7.750 -0.3571 0.09871 0.09410 -0.0284 1.0000 0.0405
-7.250 -0.3556 0.09285 0.08834 -0.0299 1.0000 0.0406
-7.000 -0.3535 0.08975 0.08529 -0.0310 1.0000 0.0406
-6.750 -0.3500 0.08652 0.08208 -0.0322 1.0000 0.0406
-6.500 -0.3498 0.08302 0.07867 -0.0225 1.0000 0.0436
-6.250 -0.3483 0.08043 0.07613 -0.0225 1.0000 0.0446
-6.000 -0.3457 0.07764 0.07338 -0.0231 1.0000 0.0452
-5.500 -0.3260 0.06653 0.06213 -0.0332 1.0000 0.0306
-5.250 -0.3133 0.06307 0.05867 -0.0342 0.9987 0.0300
-5.000 -0.2767 0.05754 0.05300 -0.0417 0.9927 0.0293
-4.750 -0.2353 0.05132 0.04655 -0.0501 0.9866 0.0289
-4.500 -0.1925 0.04414 0.03897 -0.0582 0.9802 0.0301
-4.250 -0.1503 0.03698 0.03112 -0.0645 0.9751 0.0310
-4.000 -0.1178 0.03298 0.02676 -0.0674 0.9690 0.0318
-3.750 -0.0826 0.03054 0.02401 -0.0701 0.9637 0.0336
-3.500 -0.0487 0.02805 0.02103 -0.0718 0.9567 0.0378
-3.250 -0.0087 0.02482 0.01690 -0.0740 0.9523 0.0408
-3.000 0.0209 0.02365 0.01568 -0.0748 0.9435 0.0453
-2.750 0.0603 0.02201 0.01352 -0.0767 0.9381 0.0510
-2.500 0.0911 0.02081 0.01212 -0.0772 0.9286 0.0570
-2.250 0.1309 0.01967 0.01074 -0.0791 0.9228 0.0633
-2.000 0.1615 0.01876 0.00966 -0.0793 0.9118 0.0696
-1.750 0.1948 0.01786 0.00871 -0.0801 0.9019 0.0740
-1.500 0.2315 0.01715 0.00787 -0.0813 0.8927 0.0804
-1.250 0.2624 0.01640 0.00718 -0.0816 0.8799 0.0873
-1.000 0.2939 0.01587 0.00657 -0.0818 0.8659 0.0930
-0.750 0.3267 0.01533 0.00603 -0.0824 0.8509 0.1011
-0.500 0.3583 0.01488 0.00561 -0.0827 0.8331 0.1197
-0.250 0.3918 0.01430 0.00527 -0.0834 0.8140 0.1875
0.000 0.4255 0.01338 0.00506 -0.0843 0.7932 0.4347
0.250 0.4769 0.01211 0.00472 -0.0883 0.7685 1.0000
0.500 0.5086 0.01214 0.00449 -0.0885 0.7402 1.0000
0.750 0.5385 0.01224 0.00432 -0.0884 0.7105 1.0000
1.000 0.5669 0.01239 0.00422 -0.0880 0.6806 1.0000
1.250 0.5940 0.01259 0.00419 -0.0875 0.6522 1.0000
1.500 0.6204 0.01282 0.00420 -0.0869 0.6263 1.0000
1.750 0.6462 0.01307 0.00425 -0.0862 0.6032 1.0000
2.000 0.6719 0.01335 0.00434 -0.0856 0.5835 1.0000
2.250 0.6973 0.01364 0.00447 -0.0849 0.5650 1.0000
2.500 0.7223 0.01394 0.00463 -0.0842 0.5467 1.0000
2.750 0.7470 0.01427 0.00482 -0.0834 0.5285 1.0000
3.000 0.7714 0.01460 0.00501 -0.0826 0.5106 1.0000
3.250 0.7955 0.01493 0.00522 -0.0817 0.4933 1.0000
3.500 0.8195 0.01525 0.00545 -0.0809 0.4764 1.0000
3.750 0.8433 0.01554 0.00571 -0.0800 0.4593 1.0000
4.000 0.8673 0.01583 0.00596 -0.0792 0.4438 1.0000
4.250 0.8914 0.01613 0.00624 -0.0784 0.4305 1.0000
4.500 0.9154 0.01643 0.00655 -0.0776 0.4171 1.0000
4.750 0.9391 0.01672 0.00686 -0.0768 0.4029 1.0000
5.000 0.9625 0.01703 0.00717 -0.0759 0.3881 1.0000
5.250 0.9856 0.01736 0.00753 -0.0750 0.3726 1.0000
5.500 1.0084 0.01770 0.00789 -0.0741 0.3567 1.0000
5.750 1.0311 0.01806 0.00828 -0.0731 0.3400 1.0000
6.000 1.0533 0.01844 0.00870 -0.0721 0.3215 1.0000
6.250 1.0748 0.01888 0.00917 -0.0710 0.3013 1.0000
6.500 1.0958 0.01937 0.00966 -0.0698 0.2787 1.0000
6.750 1.1155 0.01995 0.01018 -0.0685 0.2540 1.0000
7.000 1.1351 0.02058 0.01079 -0.0672 0.2303 1.0000
7.250 1.1537 0.02131 0.01148 -0.0658 0.2120 1.0000
7.500 1.1726 0.02205 0.01221 -0.0645 0.1991 1.0000
7.750 1.1916 0.02279 0.01301 -0.0631 0.1898 1.0000
8.250 1.2291 0.02438 0.01471 -0.0604 0.1767 1.0000
8.500 1.2473 0.02522 0.01564 -0.0590 0.1711 1.0000
8.750 1.2658 0.02609 0.01660 -0.0577 0.1662 1.0000
9.000 1.2851 0.02693 0.01760 -0.0565 0.1617 1.0000
9.250 1.3038 0.02785 0.01863 -0.0552 0.1579 1.0000
9.500 1.3208 0.02878 0.01968 -0.0538 0.1517 1.0000
9.750 1.3335 0.02962 0.02060 -0.0519 0.1419 1.0000
10.000 1.3441 0.03037 0.02158 -0.0498 0.1301 1.0000
10.250 1.3534 0.03118 0.02253 -0.0475 0.1189 1.0000
10.500 1.3608 0.03208 0.02355 -0.0450 0.1091 1.0000
10.750 1.3694 0.03300 0.02465 -0.0428 0.0986 1.0000
11.000 1.3806 0.03386 0.02578 -0.0409 0.0812 1.0000
11.250 1.3831 0.03541 0.02723 -0.0385 0.0533 1.0000
11.500 1.3760 0.03790 0.02954 -0.0356 0.0401 1.0000
11.750 1.3682 0.04063 0.03231 -0.0331 0.0337 1.0000
12.000 1.3614 0.04345 0.03525 -0.0312 0.0302 1.0000
12.250 1.3541 0.04652 0.03850 -0.0298 0.0277 1.0000
12.500 1.3443 0.05010 0.04224 -0.0291 0.0263 1.0000
12.750 1.3323 0.05426 0.04656 -0.0291 0.0253 1.0000
13.000 1.3197 0.05889 0.05133 -0.0299 0.0246 1.0000
13.250 1.3092 0.06361 0.05628 -0.0311 0.0239 1.0000
13.500 1.2971 0.06888 0.06176 -0.0329 0.0233 1.0000
13.750 1.2843 0.07454 0.06762 -0.0352 0.0227 1.0000
14.000 1.2702 0.08061 0.07387 -0.0377 0.0223 1.0000
14.250 1.2563 0.08685 0.08029 -0.0404 0.0221 1.0000
14.500 1.2418 0.09336 0.08701 -0.0434 0.0218 1.0000
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Polar data table (+)
Polar graphs
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