MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 200,000 Max Cl/Cd: 86.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh38-il-200000.txt Download as CSV file: xf-mh38-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 38 9.68%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.4650 0.01058 0.00466 -0.0976 0.7596 1.0000
0.500 0.4921 0.01068 0.00468 -0.0974 0.7533 1.0000
0.750 0.5194 0.01080 0.00471 -0.0973 0.7476 1.0000
1.000 0.5463 0.01092 0.00479 -0.0971 0.7407 1.0000
1.250 0.5740 0.01102 0.00480 -0.0969 0.7355 1.0000
1.500 0.6005 0.01116 0.00493 -0.0968 0.7279 1.0000
1.750 0.6284 0.01124 0.00493 -0.0966 0.7227 1.0000
2.000 0.6548 0.01139 0.00510 -0.0964 0.7148 1.0000
2.250 0.6827 0.01147 0.00513 -0.0962 0.7093 1.0000
2.500 0.7090 0.01162 0.00531 -0.0960 0.7010 1.0000
3.000 0.7631 0.01182 0.00551 -0.0956 0.6864 1.0000
3.250 0.7904 0.01191 0.00561 -0.0953 0.6794 1.0000
3.500 0.8172 0.01200 0.00573 -0.0950 0.6710 1.0000
3.750 0.8438 0.01211 0.00587 -0.0947 0.6624 1.0000
4.000 0.8715 0.01216 0.00590 -0.0945 0.6548 1.0000
4.250 0.8974 0.01226 0.00613 -0.0941 0.6447 1.0000
4.500 0.9239 0.01236 0.00627 -0.0937 0.6350 1.0000
4.750 0.9508 0.01242 0.00636 -0.0934 0.6256 1.0000
5.000 0.9772 0.01248 0.00647 -0.0929 0.6146 1.0000
5.250 1.0029 0.01255 0.00663 -0.0924 0.6022 1.0000
5.500 1.0285 0.01261 0.00675 -0.0918 0.5886 1.0000
5.750 1.0539 0.01265 0.00689 -0.0911 0.5732 1.0000
6.000 1.0779 0.01270 0.00704 -0.0903 0.5525 1.0000
6.250 1.1011 0.01277 0.00712 -0.0892 0.5261 1.0000
6.500 1.1236 0.01294 0.00730 -0.0880 0.4964 1.0000
6.750 1.1449 0.01325 0.00757 -0.0868 0.4612 1.0000
7.000 1.1625 0.01382 0.00794 -0.0850 0.4086 1.0000
7.250 1.1751 0.01479 0.00857 -0.0827 0.3350 1.0000
7.500 1.1814 0.01632 0.00955 -0.0798 0.2430 1.0000
7.750 1.1791 0.01859 0.01104 -0.0760 0.1280 1.0000
8.000 1.1689 0.02152 0.01321 -0.0711 0.0442 1.0000
8.250 1.1624 0.02373 0.01545 -0.0662 0.0288 1.0000
8.500 1.1688 0.02502 0.01683 -0.0634 0.0228 1.0000
8.750 1.1605 0.02746 0.01932 -0.0593 0.0195 1.0000
9.000 1.1677 0.02898 0.02098 -0.0570 0.0180 1.0000
9.250 1.1737 0.03082 0.02292 -0.0547 0.0170 1.0000
9.500 1.1822 0.03276 0.02496 -0.0526 0.0160 1.0000
9.750 1.1948 0.03474 0.02704 -0.0509 0.0153 1.0000
10.000 1.2124 0.03688 0.02931 -0.0495 0.0149 1.0000
10.250 1.2346 0.03934 0.03197 -0.0485 0.0147 1.0000
10.500 1.2576 0.04252 0.03546 -0.0476 0.0149 1.0000
10.750 1.2737 0.04641 0.03974 -0.0463 0.0155 1.0000
11.000 1.2785 0.05041 0.04412 -0.0443 0.0162 1.0000
11.250 1.2754 0.05450 0.04857 -0.0421 0.0168 1.0000
11.500 1.2673 0.05851 0.05289 -0.0401 0.0172 1.0000
11.750 1.2566 0.06254 0.05718 -0.0385 0.0175 1.0000
12.000 1.2433 0.06677 0.06167 -0.0374 0.0177 1.0000
12.250 1.2273 0.07162 0.06675 -0.0369 0.0181 1.0000
12.500 1.2098 0.07671 0.07207 -0.0371 0.0183 1.0000
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Polar data table (+)
Polar graphs
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