MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 100,000 Max Cl/Cd: 61.39 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh38-il-100000.txt Download as CSV file: xf-mh38-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3242 0.10406 0.09941 -0.0380 1.0000 0.0826
-8.750 -0.3363 0.10269 0.09817 -0.0418 1.0000 0.0838
-8.500 -0.3504 0.10125 0.09689 -0.0445 1.0000 0.0842
-8.250 -0.3189 0.09435 0.08992 -0.0396 1.0000 0.0876
-8.000 -0.3163 0.09175 0.08740 -0.0390 1.0000 0.0902
-7.750 -0.3222 0.08969 0.08546 -0.0383 1.0000 0.0928
-7.500 -0.3395 0.08880 0.08473 -0.0358 1.0000 0.0942
-7.250 -0.3688 0.08917 0.08527 -0.0302 1.0000 0.0943
-7.000 -0.3948 0.08932 0.08553 -0.0254 1.0000 0.0940
-6.750 -0.4171 0.08860 0.08492 -0.0234 1.0000 0.0950
-6.500 -0.4072 0.08231 0.07860 -0.0414 0.9913 0.0983
-6.250 -0.3872 0.07888 0.07520 -0.0369 0.9875 0.1012
-6.000 -0.3556 0.07113 0.06720 -0.0581 0.9761 0.1117
-5.750 -0.3347 0.06727 0.06343 -0.0558 0.9715 0.1141
-5.500 -0.3006 0.04880 0.04417 -0.0754 0.9630 0.0601
-5.250 -0.2683 0.04171 0.03657 -0.0809 0.9571 0.0538
-5.000 -0.2349 0.03588 0.02993 -0.0854 0.9513 0.0553
-4.750 -0.2006 0.03134 0.02432 -0.0879 0.9451 0.0578
-4.500 -0.1615 0.02812 0.02080 -0.0910 0.9414 0.0668
-4.250 -0.1328 0.02619 0.01847 -0.0916 0.9343 0.0785
-4.000 -0.0935 0.02461 0.01636 -0.0937 0.9295 0.0985
-3.750 -0.0598 0.02345 0.01517 -0.0951 0.9239 0.1190
-3.500 -0.0265 0.02242 0.01402 -0.0962 0.9178 0.1421
-3.250 0.0164 0.02158 0.01315 -0.0992 0.9142 0.1771
-3.000 0.0408 0.02109 0.01269 -0.0988 0.9062 0.2049
-2.750 0.0804 0.02041 0.01209 -0.1011 0.9018 0.2492
-2.500 0.1073 0.01999 0.01184 -0.1012 0.8949 0.2945
-2.250 0.1400 0.01940 0.01156 -0.1022 0.8893 0.3661
-2.000 0.1700 0.01880 0.01145 -0.1026 0.8838 0.4801
-1.500 0.2442 0.01729 0.01114 -0.1036 0.8743 1.0000
-1.250 0.2683 0.01763 0.01119 -0.1035 0.8660 1.0000
-1.000 0.3037 0.01772 0.01101 -0.1049 0.8607 1.0000
-0.750 0.3265 0.01810 0.01120 -0.1043 0.8524 1.0000
-0.500 0.3604 0.01819 0.01108 -0.1053 0.8470 1.0000
-0.250 0.3825 0.01861 0.01137 -0.1047 0.8385 1.0000
0.000 0.4156 0.01869 0.01131 -0.1054 0.8332 1.0000
0.250 0.4371 0.01915 0.01167 -0.1046 0.8245 1.0000
0.500 0.4700 0.01921 0.01162 -0.1052 0.8193 1.0000
0.750 0.4909 0.01971 0.01205 -0.1044 0.8103 1.0000
1.000 0.5239 0.01973 0.01198 -0.1048 0.8053 1.0000
1.250 0.5443 0.02026 0.01248 -0.1039 0.7959 1.0000
1.500 0.5777 0.02022 0.01239 -0.1043 0.7912 1.0000
1.750 0.5977 0.02078 0.01294 -0.1034 0.7813 1.0000
2.000 0.6286 0.02083 0.01295 -0.1034 0.7758 1.0000
2.250 0.6514 0.02125 0.01338 -0.1027 0.7666 1.0000
2.500 0.6758 0.02161 0.01378 -0.1021 0.7582 1.0000
2.750 0.7058 0.02162 0.01379 -0.1019 0.7517 1.0000
3.000 0.7280 0.02208 0.01429 -0.1011 0.7419 1.0000
3.250 0.7612 0.02184 0.01406 -0.1011 0.7366 1.0000
3.500 0.7827 0.02230 0.01463 -0.1001 0.7258 1.0000
3.750 0.8073 0.02257 0.01496 -0.0994 0.7164 1.0000
4.000 0.8394 0.02229 0.01472 -0.0991 0.7099 1.0000
4.250 0.8624 0.02260 0.01513 -0.0982 0.6988 1.0000
4.500 0.8876 0.02275 0.01542 -0.0973 0.6886 1.0000
4.750 0.9212 0.02226 0.01499 -0.0970 0.6818 1.0000
5.000 0.9452 0.02241 0.01527 -0.0960 0.6699 1.0000
5.250 0.9703 0.02246 0.01544 -0.0951 0.6581 1.0000
5.500 0.9966 0.02238 0.01549 -0.0941 0.6461 1.0000
5.750 1.0237 0.02219 0.01543 -0.0932 0.6337 1.0000
6.000 1.0511 0.02190 0.01534 -0.0921 0.6201 1.0000
6.250 1.0787 0.02151 0.01508 -0.0910 0.6050 1.0000
6.500 1.1076 0.02086 0.01453 -0.0898 0.5880 1.0000
6.750 1.1313 0.02037 0.01418 -0.0880 0.5645 1.0000
7.000 1.1548 0.01969 0.01356 -0.0859 0.5349 1.0000
7.250 1.1741 0.01938 0.01333 -0.0835 0.4977 1.0000
7.500 1.1904 0.01939 0.01328 -0.0808 0.4498 1.0000
7.750 1.1991 0.02001 0.01365 -0.0773 0.3771 1.0000
8.000 1.1935 0.02184 0.01480 -0.0725 0.2606 1.0000
8.250 1.1725 0.02524 0.01702 -0.0666 0.1300 1.0000
8.500 1.1564 0.02825 0.01945 -0.0611 0.0830 1.0000
8.750 1.1483 0.03082 0.02183 -0.0571 0.0647 1.0000
9.000 1.1463 0.03320 0.02420 -0.0538 0.0540 1.0000
9.250 1.1497 0.03547 0.02649 -0.0514 0.0456 1.0000
9.500 1.1623 0.03832 0.02918 -0.0494 0.0396 1.0000
9.750 1.1937 0.04070 0.03175 -0.0486 0.0360 1.0000
10.000 1.2166 0.04313 0.03431 -0.0479 0.0323 1.0000
10.250 1.2607 0.04904 0.04036 -0.0502 0.0289 1.0000
10.500 1.2752 0.05267 0.04437 -0.0489 0.0287 1.0000
10.750 1.2832 0.05673 0.04881 -0.0471 0.0288 1.0000
11.000 1.2896 0.06203 0.05450 -0.0458 0.0291 1.0000
11.250 1.2864 0.06443 0.05718 -0.0429 0.0294 1.0000
11.500 1.2793 0.06670 0.05973 -0.0401 0.0298 1.0000
11.750 1.2682 0.06923 0.06259 -0.0376 0.0303 1.0000
12.000 1.2511 0.07279 0.06654 -0.0357 0.0312 1.0000
12.250 1.2256 0.07730 0.07143 -0.0349 0.0319 1.0000
12.500 1.2001 0.08268 0.07716 -0.0352 0.0326 1.0000
12.750 1.1759 0.08851 0.08327 -0.0365 0.0332 1.0000
13.000 1.1515 0.09489 0.08989 -0.0388 0.0337 1.0000
13.250 1.1267 0.10191 0.09712 -0.0422 0.0341 1.0000
13.500 1.1025 0.10957 0.10495 -0.0466 0.0346 1.0000
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Polar data table (+)
Polar graphs
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