MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 50,000 Max Cl/Cd: 35.2 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh32-il-50000.txt Download as CSV file: xf-mh32-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4293 0.10315 0.09665 -0.0181 1.0000 0.2241
-8.000 -0.4143 0.09879 0.09230 -0.0169 1.0000 0.2364
-7.750 -0.4112 0.09572 0.08932 -0.0163 1.0000 0.2499
-7.500 -0.4060 0.09250 0.08616 -0.0155 1.0000 0.2626
-7.250 -0.3317 0.08026 0.07442 -0.0168 1.0000 0.2942
-7.000 -0.3400 0.07796 0.07224 -0.0156 1.0000 0.3066
-6.750 -0.3388 0.07455 0.06892 -0.0139 1.0000 0.3201
-6.500 -0.3363 0.07117 0.06562 -0.0120 1.0000 0.3332
-6.250 -0.4088 0.07902 0.07314 -0.0077 1.0000 0.3381
-6.000 -0.4072 0.07623 0.07045 -0.0056 1.0000 0.3545
-4.750 -0.3891 0.04437 0.03696 -0.0406 1.0000 0.1126
-4.500 -0.3706 0.04006 0.03214 -0.0405 1.0000 0.1054
-4.250 -0.3484 0.03640 0.02772 -0.0401 1.0000 0.1000
-4.000 -0.3261 0.03323 0.02399 -0.0392 1.0000 0.0990
-3.750 -0.3018 0.03061 0.02070 -0.0383 1.0000 0.1014
-3.500 -0.2796 0.02850 0.01847 -0.0374 1.0000 0.1129
-3.250 -0.2548 0.02625 0.01599 -0.0362 1.0000 0.1244
-3.000 -0.2310 0.02450 0.01419 -0.0350 1.0000 0.1519
-2.750 -0.2058 0.02258 0.01242 -0.0338 1.0000 0.2000
-2.500 -0.1823 0.01956 0.01096 -0.0323 1.0000 0.4273
-2.250 -0.1452 0.01725 0.01041 -0.0288 1.0000 1.0000
-2.000 -0.1255 0.01725 0.00976 -0.0284 1.0000 1.0000
-1.750 -0.1056 0.01735 0.00930 -0.0279 1.0000 1.0000
-1.500 -0.0856 0.01751 0.00903 -0.0273 1.0000 1.0000
-1.250 -0.0657 0.01771 0.00888 -0.0267 1.0000 1.0000
-1.000 -0.0459 0.01795 0.00881 -0.0261 1.0000 1.0000
-0.750 -0.0263 0.01824 0.00883 -0.0256 1.0000 1.0000
-0.500 -0.0068 0.01858 0.00891 -0.0251 1.0000 1.0000
-0.250 0.0124 0.01896 0.00904 -0.0246 1.0000 1.0000
0.000 0.0313 0.01938 0.00929 -0.0242 1.0000 1.0000
0.250 0.0498 0.01986 0.00960 -0.0238 1.0000 1.0000
0.500 0.0681 0.02039 0.00999 -0.0234 1.0000 1.0000
0.750 0.0860 0.02098 0.01045 -0.0231 1.0000 1.0000
1.000 0.1035 0.02163 0.01097 -0.0229 1.0000 1.0000
1.250 0.1207 0.02234 0.01159 -0.0228 1.0000 1.0000
1.500 0.1578 0.02346 0.01265 -0.0265 0.9904 1.0000
1.750 0.2136 0.02487 0.01400 -0.0334 0.9712 1.0000
2.000 0.2645 0.02606 0.01516 -0.0391 0.9512 1.0000
2.250 0.3155 0.02710 0.01623 -0.0445 0.9305 1.0000
2.500 0.3612 0.02795 0.01714 -0.0486 0.9090 1.0000
2.750 0.4134 0.02866 0.01796 -0.0534 0.8881 1.0000
3.000 0.4525 0.02923 0.01862 -0.0557 0.8653 1.0000
3.250 0.5013 0.02959 0.01913 -0.0592 0.8439 1.0000
3.500 0.5486 0.02973 0.01951 -0.0620 0.8215 1.0000
3.750 0.5914 0.02977 0.01973 -0.0637 0.7982 1.0000
4.000 0.6414 0.02928 0.01947 -0.0656 0.7767 1.0000
4.250 0.6835 0.02874 0.01921 -0.0658 0.7530 1.0000
4.500 0.7200 0.02823 0.01890 -0.0651 0.7277 1.0000
4.750 0.7566 0.02754 0.01842 -0.0640 0.7013 1.0000
5.000 0.7920 0.02679 0.01785 -0.0624 0.6731 1.0000
5.250 0.8266 0.02603 0.01728 -0.0604 0.6429 1.0000
5.500 0.8518 0.02597 0.01732 -0.0580 0.6077 1.0000
5.750 0.8792 0.02583 0.01720 -0.0556 0.5714 1.0000
6.000 0.9044 0.02594 0.01728 -0.0532 0.5325 1.0000
6.250 0.9268 0.02633 0.01762 -0.0508 0.4914 1.0000
6.500 0.9473 0.02694 0.01828 -0.0483 0.4487 1.0000
6.750 0.9667 0.02772 0.01899 -0.0459 0.4049 1.0000
7.000 0.9852 0.02866 0.01981 -0.0435 0.3607 1.0000
7.250 1.0032 0.02979 0.02075 -0.0411 0.3168 1.0000
7.500 1.0202 0.03120 0.02192 -0.0389 0.2739 1.0000
7.750 1.0354 0.03295 0.02353 -0.0366 0.2326 1.0000
8.000 1.0487 0.03478 0.02527 -0.0342 0.1950 1.0000
8.250 1.0642 0.03724 0.02767 -0.0322 0.1642 1.0000
8.500 1.0809 0.03994 0.03028 -0.0305 0.1392 1.0000
8.750 1.0964 0.04357 0.03430 -0.0285 0.1242 1.0000
9.000 1.1058 0.04647 0.03750 -0.0263 0.1093 1.0000
9.250 1.1207 0.05060 0.04185 -0.0248 0.0999 1.0000
9.500 1.1187 0.05494 0.04694 -0.0219 0.0965 1.0000
9.750 1.1282 0.05843 0.05041 -0.0205 0.0871 1.0000
10.000 1.1173 0.06261 0.05518 -0.0178 0.0855 1.0000
10.250 1.1041 0.06701 0.05999 -0.0155 0.0847 1.0000
10.500 1.0881 0.07142 0.06469 -0.0136 0.0849 1.0000
10.750 1.0677 0.07569 0.06917 -0.0119 0.0852 1.0000
11.000 1.0481 0.08033 0.07396 -0.0114 0.0860 1.0000
11.250 1.0283 0.08554 0.07929 -0.0121 0.0867 1.0000
11.500 1.0118 0.09131 0.08513 -0.0137 0.0874 1.0000
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Polar data table (+)
Polar graphs
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