MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 50,000 Max Cl/Cd: 33.95 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh201-il-50000.txt Download as CSV file: xf-mh201-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 201 13.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3774 0.10865 0.10218 -0.0274 1.0000 0.2965
-8.500 -0.3557 0.10407 0.09760 -0.0257 1.0000 0.3050
-8.250 -0.3690 0.10212 0.09579 -0.0240 1.0000 0.3155
-8.000 -0.3649 0.09930 0.09302 -0.0223 1.0000 0.3227
-7.500 -0.3815 0.09455 0.08849 -0.0182 1.0000 0.3346
-7.250 -0.3929 0.09231 0.08636 -0.0160 1.0000 0.3367
-7.000 -0.4094 0.09015 0.08432 -0.0138 1.0000 0.3357
-6.750 -0.5694 0.07122 0.06533 -0.0360 1.0000 0.1357
-6.500 -0.5815 0.06519 0.05898 -0.0373 1.0000 0.1211
-6.250 -0.5850 0.05909 0.05232 -0.0384 1.0000 0.1093
-6.000 -0.5780 0.05433 0.04717 -0.0386 1.0000 0.1032
-5.750 -0.5648 0.04971 0.04165 -0.0392 1.0000 0.0970
-5.500 -0.5477 0.04625 0.03774 -0.0391 1.0000 0.0967
-5.250 -0.5275 0.04317 0.03416 -0.0390 1.0000 0.0970
-5.000 -0.5048 0.04047 0.03086 -0.0387 1.0000 0.0981
-4.750 -0.4821 0.03762 0.02774 -0.0383 1.0000 0.0996
-4.500 -0.4599 0.03554 0.02555 -0.0375 1.0000 0.1032
-4.250 -0.4366 0.03394 0.02361 -0.0367 1.0000 0.1109
-4.000 -0.4148 0.03226 0.02193 -0.0354 1.0000 0.1205
-3.750 -0.3934 0.03088 0.02056 -0.0339 1.0000 0.1374
-3.500 -0.3727 0.02946 0.01933 -0.0322 1.0000 0.1681
-3.250 -0.3491 0.02593 0.01744 -0.0319 1.0000 0.3385
-3.000 -0.3614 0.02568 0.01931 -0.0198 1.0000 0.6750
-2.750 -0.3688 0.02694 0.02052 -0.0098 1.0000 0.7579
-2.500 -0.3783 0.02768 0.02120 0.0003 1.0000 0.8152
-2.250 -0.3866 0.02794 0.02140 0.0101 1.0000 0.8664
-2.000 -0.1896 0.03080 0.02288 -0.0134 1.0000 0.9842
-1.750 -0.1344 0.03071 0.02237 -0.0213 1.0000 1.0000
-1.500 -0.1374 0.03029 0.02184 -0.0186 1.0000 1.0000
-1.250 -0.1399 0.02992 0.02136 -0.0159 1.0000 1.0000
-1.000 -0.1418 0.02957 0.02089 -0.0132 1.0000 1.0000
-0.750 -0.1431 0.02925 0.02047 -0.0105 1.0000 1.0000
-0.500 -0.1436 0.02895 0.02008 -0.0079 1.0000 1.0000
-0.250 -0.1428 0.02870 0.01973 -0.0055 1.0000 1.0000
0.000 -0.1387 0.02855 0.01948 -0.0036 1.0000 1.0000
0.250 -0.1290 0.02861 0.01941 -0.0027 1.0000 1.0000
0.500 -0.1148 0.02887 0.01953 -0.0027 1.0000 1.0000
0.750 -0.0975 0.02929 0.01983 -0.0031 1.0000 1.0000
1.000 -0.0785 0.02985 0.02026 -0.0039 1.0000 1.0000
1.250 -0.0350 0.03141 0.02166 -0.0092 0.9889 1.0000
1.500 0.0213 0.03339 0.02346 -0.0164 0.9703 1.0000
1.750 0.0629 0.03461 0.02458 -0.0209 0.9533 1.0000
2.000 0.1051 0.03586 0.02573 -0.0253 0.9366 1.0000
2.250 0.1474 0.03708 0.02688 -0.0295 0.9199 1.0000
2.500 0.1894 0.03825 0.02799 -0.0335 0.9032 1.0000
2.750 0.2323 0.03939 0.02910 -0.0374 0.8865 1.0000
3.000 0.2685 0.04034 0.03003 -0.0401 0.8691 1.0000
3.250 0.3013 0.04121 0.03090 -0.0422 0.8512 1.0000
3.500 0.3359 0.04208 0.03178 -0.0444 0.8331 1.0000
3.750 0.3722 0.04292 0.03266 -0.0467 0.8151 1.0000
4.000 0.4113 0.04365 0.03344 -0.0491 0.7970 1.0000
4.250 0.4526 0.04425 0.03409 -0.0515 0.7793 1.0000
4.500 0.4958 0.04468 0.03462 -0.0538 0.7621 1.0000
4.750 0.5188 0.04540 0.03540 -0.0538 0.7416 1.0000
5.000 0.5523 0.04580 0.03589 -0.0548 0.7223 1.0000
5.250 0.5926 0.04585 0.03606 -0.0560 0.7038 1.0000
5.500 0.6384 0.04541 0.03578 -0.0574 0.6861 1.0000
5.750 0.6882 0.04442 0.03496 -0.0586 0.6692 1.0000
6.000 0.7051 0.04513 0.03579 -0.0574 0.6462 1.0000
6.250 0.7539 0.04363 0.03447 -0.0578 0.6282 1.0000
6.500 0.8161 0.04073 0.03183 -0.0584 0.6114 1.0000
6.750 0.9126 0.03578 0.02720 -0.0621 0.5925 1.0000
7.000 0.9550 0.03439 0.02595 -0.0618 0.5651 1.0000
7.250 1.0102 0.03253 0.02413 -0.0628 0.5337 1.0000
7.500 1.0559 0.03165 0.02318 -0.0633 0.4993 1.0000
7.750 1.0819 0.03200 0.02347 -0.0621 0.4660 1.0000
8.000 1.1073 0.03262 0.02402 -0.0610 0.4336 1.0000
8.250 1.1315 0.03349 0.02478 -0.0600 0.4028 1.0000
8.500 1.1559 0.03453 0.02570 -0.0591 0.3738 1.0000
8.750 1.1781 0.03579 0.02687 -0.0581 0.3471 1.0000
9.000 1.1937 0.03737 0.02854 -0.0564 0.3240 1.0000
9.250 1.2174 0.03886 0.02993 -0.0557 0.3014 1.0000
9.500 1.2356 0.04064 0.03173 -0.0545 0.2819 1.0000
9.750 1.2501 0.04261 0.03384 -0.0529 0.2650 1.0000
10.000 1.2650 0.04467 0.03602 -0.0515 0.2494 1.0000
10.250 1.2799 0.04682 0.03830 -0.0500 0.2351 1.0000
10.500 1.2968 0.04909 0.04065 -0.0489 0.2219 1.0000
10.750 1.3161 0.05135 0.04292 -0.0482 0.2087 1.0000
11.000 1.3008 0.05457 0.04671 -0.0438 0.2033 1.0000
11.250 1.3179 0.05709 0.04925 -0.0429 0.1925 1.0000
11.500 1.2962 0.06060 0.05321 -0.0384 0.1889 1.0000
11.750 1.3183 0.06326 0.05585 -0.0382 0.1786 1.0000
12.000 1.2886 0.06705 0.06001 -0.0335 0.1775 1.0000
12.250 1.2561 0.07146 0.06470 -0.0299 0.1770 1.0000
12.500 1.2206 0.07675 0.07023 -0.0276 0.1773 1.0000
12.750 1.1825 0.08322 0.07689 -0.0269 0.1781 1.0000
13.000 1.1440 0.09098 0.08476 -0.0281 0.1792 1.0000
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Polar data table (+)
Polar graphs
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