MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 50,000 Max Cl/Cd: 33.84 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh22-il-50000.txt Download as CSV file: xf-mh22-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 22 7.2%
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5096 0.09174 0.08576 0.0076 1.0000 0.2286
-7.000 -0.5146 0.08885 0.08299 0.0060 1.0000 0.2390
-6.750 -0.5101 0.08522 0.07928 0.0055 1.0000 0.2525
-6.500 -0.5007 0.08148 0.07559 0.0061 1.0000 0.2688
-6.250 -0.5081 0.07916 0.07336 0.0028 1.0000 0.2899
-6.000 -0.4988 0.07569 0.06996 0.0047 1.0000 0.3163
-5.750 -0.4799 0.07165 0.06599 0.0101 1.0000 0.3504
-5.250 -0.4393 0.05240 0.04566 -0.0257 1.0000 0.1261
-5.000 -0.4170 0.04613 0.03875 -0.0281 1.0000 0.1016
-4.750 -0.3971 0.04196 0.03423 -0.0283 1.0000 0.0991
-4.500 -0.3758 0.03815 0.02997 -0.0282 1.0000 0.0988
-4.250 -0.3532 0.03462 0.02592 -0.0276 1.0000 0.0990
-4.000 -0.3291 0.03125 0.02200 -0.0267 1.0000 0.0983
-3.750 -0.3037 0.02825 0.01845 -0.0255 1.0000 0.1009
-3.500 -0.2784 0.02559 0.01550 -0.0242 1.0000 0.1107
-3.250 -0.2560 0.02363 0.01353 -0.0229 1.0000 0.1479
-3.000 -0.2314 0.02122 0.01130 -0.0214 1.0000 0.2128
-2.750 -0.1269 0.01490 0.00801 -0.0300 1.0000 1.0000
-2.500 -0.1074 0.01476 0.00721 -0.0291 1.0000 1.0000
-2.250 -0.0895 0.01471 0.00672 -0.0279 1.0000 1.0000
-2.000 -0.0738 0.01473 0.00638 -0.0262 1.0000 1.0000
-1.750 -0.0606 0.01482 0.00607 -0.0242 1.0000 1.0000
-1.500 -0.0494 0.01498 0.00598 -0.0220 1.0000 1.0000
-1.250 -0.0387 0.01522 0.00597 -0.0199 1.0000 1.0000
-1.000 -0.0273 0.01549 0.00600 -0.0179 1.0000 1.0000
-0.750 -0.0146 0.01579 0.00608 -0.0163 1.0000 1.0000
-0.500 -0.0008 0.01612 0.00621 -0.0149 1.0000 1.0000
-0.250 0.0138 0.01648 0.00639 -0.0137 1.0000 1.0000
0.000 0.0291 0.01686 0.00661 -0.0127 1.0000 1.0000
0.250 0.0448 0.01728 0.00679 -0.0119 1.0000 1.0000
0.500 0.0607 0.01774 0.00712 -0.0112 1.0000 1.0000
0.750 0.0768 0.01824 0.00752 -0.0106 1.0000 1.0000
1.000 0.1009 0.01887 0.00806 -0.0117 0.9965 1.0000
1.250 0.1588 0.01985 0.00900 -0.0191 0.9782 1.0000
1.500 0.2143 0.02069 0.00988 -0.0257 0.9588 1.0000
1.750 0.2712 0.02146 0.01069 -0.0323 0.9393 1.0000
2.000 0.3254 0.02209 0.01143 -0.0380 0.9184 1.0000
2.250 0.3818 0.02261 0.01211 -0.0438 0.8972 1.0000
2.500 0.4390 0.02297 0.01276 -0.0490 0.8760 1.0000
2.750 0.4783 0.02341 0.01337 -0.0508 0.8526 1.0000
3.000 0.5151 0.02383 0.01397 -0.0517 0.8292 1.0000
3.250 0.5486 0.02421 0.01453 -0.0516 0.8057 1.0000
3.500 0.5796 0.02450 0.01500 -0.0506 0.7825 1.0000
3.750 0.6037 0.02494 0.01578 -0.0486 0.7574 1.0000
4.000 0.6263 0.02536 0.01638 -0.0463 0.7318 1.0000
4.250 0.6484 0.02573 0.01693 -0.0437 0.7057 1.0000
4.500 0.6703 0.02600 0.01739 -0.0408 0.6789 1.0000
4.750 0.6923 0.02612 0.01770 -0.0376 0.6511 1.0000
5.000 0.7125 0.02635 0.01815 -0.0346 0.6195 1.0000
5.250 0.7344 0.02614 0.01813 -0.0309 0.5867 1.0000
5.500 0.7557 0.02572 0.01789 -0.0270 0.5480 1.0000
5.750 0.7759 0.02470 0.01719 -0.0222 0.4972 1.0000
6.000 0.7905 0.02336 0.01563 -0.0165 0.4156 1.0000
6.250 0.7896 0.02469 0.01574 -0.0110 0.2366 1.0000
6.500 0.7952 0.02880 0.01857 -0.0078 0.1256 1.0000
6.750 0.8166 0.03213 0.02168 -0.0056 0.0935 1.0000
7.000 0.8420 0.03548 0.02514 -0.0040 0.0799 1.0000
7.250 0.8617 0.03843 0.02830 -0.0028 0.0679 1.0000
7.500 0.8829 0.04183 0.03197 -0.0016 0.0628 1.0000
7.750 0.9016 0.04588 0.03645 -0.0004 0.0620 1.0000
8.000 0.9139 0.05024 0.04147 0.0010 0.0628 1.0000
8.250 0.9191 0.05504 0.04696 0.0022 0.0647 1.0000
8.500 0.9199 0.06001 0.05243 0.0030 0.0668 1.0000
8.750 0.9166 0.06498 0.05776 0.0034 0.0687 1.0000
9.000 0.9124 0.06993 0.06292 0.0036 0.0704 1.0000
9.250 0.9242 0.07566 0.06866 0.0038 0.0728 1.0000
9.500 0.8898 0.07932 0.07271 0.0027 0.0741 1.0000
9.750 0.8589 0.08452 0.07802 -0.0006 0.0752 1.0000
10.000 0.8281 0.09235 0.08588 -0.0080 0.0774 1.0000
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Polar data table (+)
Polar graphs
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