MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 50,000 Max Cl/Cd: 16.06 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh91-il-50000.txt Download as CSV file: xf-mh91-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 91 14.98%
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5274 0.10893 0.10248 0.0022 1.0000 0.1622
-10.250 -0.5624 0.09536 0.08899 -0.0082 1.0000 0.1311
-10.000 -0.6403 0.08116 0.07473 -0.0209 1.0000 0.1194
-9.750 -0.6482 0.07585 0.06942 -0.0220 1.0000 0.1161
-9.500 -0.6795 0.07066 0.06412 -0.0222 1.0000 0.1130
-9.250 -0.7524 0.06618 0.05886 -0.0187 1.0000 0.1073
-9.000 -0.7401 0.06163 0.05429 -0.0184 1.0000 0.1059
-8.750 -0.7375 0.05759 0.05005 -0.0171 1.0000 0.1044
-8.500 -0.7357 0.05377 0.04594 -0.0155 1.0000 0.1029
-8.250 -0.7306 0.05020 0.04202 -0.0137 1.0000 0.1018
-8.000 -0.7224 0.04684 0.03829 -0.0119 1.0000 0.1015
-7.750 -0.7105 0.04398 0.03508 -0.0101 1.0000 0.1025
-7.500 -0.6975 0.04143 0.03213 -0.0083 1.0000 0.1049
-7.250 -0.6838 0.03927 0.02952 -0.0062 1.0000 0.1072
-7.000 -0.6603 0.03659 0.02695 -0.0057 1.0000 0.1117
-6.750 -0.6403 0.03467 0.02492 -0.0043 1.0000 0.1170
-6.500 -0.6219 0.03285 0.02310 -0.0026 1.0000 0.1247
-6.250 -0.6065 0.03150 0.02166 -0.0005 1.0000 0.1347
-6.000 -0.5903 0.03004 0.02033 0.0015 1.0000 0.1499
-5.750 -0.5783 0.02862 0.01927 0.0039 1.0000 0.1715
-5.500 -0.5734 0.02727 0.01826 0.0072 1.0000 0.2047
-5.250 -0.5794 0.02552 0.01730 0.0119 1.0000 0.2744
-5.000 -0.5980 0.02374 0.01686 0.0191 1.0000 0.4220
-4.750 -0.6067 0.02353 0.01731 0.0262 1.0000 0.5430
-4.500 -0.6038 0.02411 0.01817 0.0320 1.0000 0.6171
-4.250 -0.5958 0.02519 0.01935 0.0375 1.0000 0.6733
-4.000 -0.5768 0.02711 0.02128 0.0423 0.9981 0.7255
-3.750 -0.4651 0.03246 0.02617 0.0367 0.9834 0.7899
-3.500 -0.3013 0.03524 0.02822 0.0180 0.9706 0.8283
-3.250 -0.1748 0.03551 0.02801 0.0016 0.9544 0.8597
-3.000 -0.0451 0.03472 0.02681 -0.0163 0.9380 0.8873
-2.750 0.0519 0.03357 0.02538 -0.0291 0.9177 0.9115
-2.500 0.1335 0.03229 0.02386 -0.0390 0.8945 0.9332
-2.250 0.1830 0.03149 0.02291 -0.0435 0.8681 0.9537
-2.000 0.2297 0.03058 0.02182 -0.0472 0.8439 0.9732
-1.750 0.2763 0.02959 0.02070 -0.0516 0.8179 0.9925
-1.500 0.3031 0.02906 0.02005 -0.0524 0.7959 1.0000
-1.250 0.3148 0.02906 0.01996 -0.0505 0.7768 1.0000
-1.000 0.3273 0.02910 0.01990 -0.0488 0.7584 1.0000
-0.750 0.3401 0.02918 0.01989 -0.0471 0.7406 1.0000
-0.500 0.3536 0.02930 0.01993 -0.0455 0.7234 1.0000
-0.250 0.3679 0.02949 0.02005 -0.0441 0.7068 1.0000
0.000 0.3825 0.02972 0.02021 -0.0428 0.6907 1.0000
0.250 0.3974 0.02999 0.02041 -0.0414 0.6753 1.0000
0.500 0.4123 0.03023 0.02058 -0.0397 0.6615 1.0000
0.750 0.4272 0.03033 0.02058 -0.0376 0.6488 1.0000
1.000 0.4435 0.03083 0.02106 -0.0368 0.6337 1.0000
1.250 0.4596 0.03142 0.02163 -0.0358 0.6196 1.0000
1.500 0.4755 0.03181 0.02197 -0.0343 0.6074 1.0000
1.750 0.4918 0.03206 0.02215 -0.0324 0.5960 1.0000
2.000 0.5072 0.03299 0.02311 -0.0318 0.5823 1.0000
2.250 0.5227 0.03364 0.02375 -0.0305 0.5710 1.0000
2.500 0.5392 0.03397 0.02402 -0.0286 0.5607 1.0000
2.750 0.5515 0.03534 0.02546 -0.0280 0.5483 1.0000
3.000 0.5695 0.03546 0.02547 -0.0256 0.5401 1.0000
3.250 0.5790 0.03706 0.02717 -0.0248 0.5278 1.0000
3.500 0.5892 0.03844 0.02860 -0.0235 0.5180 1.0000
3.750 0.6028 0.03924 0.02938 -0.0217 0.5089 1.0000
4.000 0.6038 0.04154 0.03177 -0.0203 0.4988 1.0000
4.250 0.6197 0.04205 0.03224 -0.0182 0.4909 1.0000
4.500 0.6058 0.04557 0.03586 -0.0165 0.4818 1.0000
4.750 0.6166 0.04655 0.03684 -0.0143 0.4741 1.0000
5.000 0.5959 0.05017 0.04048 -0.0118 0.4668 1.0000
5.250 0.5412 0.05586 0.04616 -0.0086 0.4612 1.0000
5.500 0.6163 0.05250 0.04281 -0.0074 0.4539 1.0000
5.750 0.5210 0.06114 0.05134 -0.0038 0.4517 1.0000
6.000 0.4719 0.06575 0.05582 -0.0005 0.4505 1.0000
6.250 0.4486 0.06959 0.05958 0.0008 0.4496 1.0000
6.500 0.4395 0.07313 0.06309 0.0011 0.4506 1.0000
6.750 0.4393 0.07649 0.06644 0.0009 0.4521 1.0000
7.000 0.4460 0.07978 0.06973 0.0006 0.4534 1.0000
7.250 0.3331 0.08971 0.07965 -0.0054 0.5634 1.0000
7.500 0.3541 0.09326 0.08321 -0.0062 0.5576 1.0000
7.750 0.3550 0.09450 0.08444 -0.0052 0.5448 1.0000
8.000 0.3597 0.09676 0.08670 -0.0049 0.5358 1.0000
8.250 0.3851 0.10001 0.08997 -0.0055 0.5250 1.0000
8.500 0.3772 0.10143 0.09137 -0.0047 0.5161 1.0000
8.750 0.4097 0.10552 0.09553 -0.0058 0.5068 1.0000
9.000 0.3980 0.10633 0.09631 -0.0047 0.4951 1.0000
9.250 0.4342 0.11146 0.10149 -0.0061 0.4882 1.0000
9.500 0.4174 0.11152 0.10154 -0.0049 0.4767 1.0000
9.750 0.4410 0.11578 0.10583 -0.0058 0.4699 1.0000
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Polar data table (+)
Polar graphs
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