MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 50,000 Max Cl/Cd: 27.55 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh60-il-50000.txt Download as CSV file: xf-mh60-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 60 10.08%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4834 0.10057 0.09461 0.0149 1.0000 0.2722
-8.000 -0.4850 0.09725 0.09138 0.0134 1.0000 0.2811
-7.750 -0.4997 0.09547 0.08975 0.0111 1.0000 0.2926
-7.500 -0.4756 0.08976 0.08402 0.0115 1.0000 0.2965
-7.250 -0.4710 0.08598 0.08031 0.0102 1.0000 0.3010
-7.000 -0.5492 0.06228 0.05594 -0.0280 1.0000 0.1091
-6.750 -0.5327 0.05773 0.05145 -0.0281 1.0000 0.1066
-6.500 -0.5231 0.05268 0.04617 -0.0293 1.0000 0.1033
-6.250 -0.5192 0.04662 0.03903 -0.0305 1.0000 0.0954
-6.000 -0.5046 0.04279 0.03479 -0.0300 1.0000 0.0954
-5.750 -0.4898 0.03933 0.03086 -0.0289 1.0000 0.0956
-5.500 -0.4755 0.03623 0.02740 -0.0272 1.0000 0.0959
-5.250 -0.4618 0.03338 0.02440 -0.0253 1.0000 0.0981
-5.000 -0.4480 0.03146 0.02232 -0.0232 1.0000 0.1052
-4.750 -0.4333 0.02942 0.02002 -0.0211 1.0000 0.1131
-4.500 -0.4161 0.02747 0.01783 -0.0190 1.0000 0.1248
-4.250 -0.3996 0.02587 0.01629 -0.0171 1.0000 0.1465
-4.000 -0.3827 0.02421 0.01476 -0.0151 1.0000 0.1837
-3.750 -0.3671 0.02233 0.01343 -0.0128 1.0000 0.2706
-3.500 -0.3574 0.02105 0.01288 -0.0094 1.0000 0.3994
-3.250 -0.3475 0.02043 0.01267 -0.0057 1.0000 0.4970
-3.000 -0.3358 0.01987 0.01246 -0.0020 1.0000 0.5836
-2.750 -0.3236 0.01929 0.01223 0.0020 1.0000 0.6723
-2.500 -0.3098 0.01872 0.01206 0.0065 1.0000 0.7817
-2.250 -0.1308 0.01871 0.01125 -0.0195 1.0000 1.0000
-2.000 -0.1454 0.01845 0.01073 -0.0156 1.0000 1.0000
-1.750 -0.1420 0.01853 0.01050 -0.0134 1.0000 1.0000
-1.500 -0.1331 0.01872 0.01038 -0.0118 1.0000 1.0000
-1.250 -0.1216 0.01900 0.01038 -0.0104 1.0000 1.0000
-1.000 -0.1086 0.01933 0.01047 -0.0094 1.0000 1.0000
-0.750 -0.0848 0.01982 0.01073 -0.0104 0.9964 1.0000
-0.500 -0.0281 0.02077 0.01137 -0.0173 0.9811 1.0000
-0.250 0.0239 0.02163 0.01202 -0.0232 0.9648 1.0000
0.000 0.0757 0.02247 0.01269 -0.0289 0.9480 1.0000
0.250 0.1287 0.02329 0.01336 -0.0345 0.9311 1.0000
0.500 0.1823 0.02405 0.01403 -0.0400 0.9141 1.0000
0.750 0.2233 0.02473 0.01465 -0.0431 0.8955 1.0000
1.000 0.2712 0.02536 0.01525 -0.0471 0.8772 1.0000
1.250 0.3188 0.02591 0.01580 -0.0505 0.8596 1.0000
1.500 0.3465 0.02658 0.01645 -0.0506 0.8402 1.0000
1.750 0.3781 0.02715 0.01702 -0.0511 0.8212 1.0000
2.000 0.4126 0.02758 0.01747 -0.0514 0.8034 1.0000
2.250 0.4345 0.02822 0.01812 -0.0502 0.7838 1.0000
2.500 0.4593 0.02874 0.01868 -0.0491 0.7647 1.0000
2.750 0.4869 0.02906 0.01902 -0.0479 0.7471 1.0000
3.000 0.5089 0.02955 0.01955 -0.0462 0.7282 1.0000
3.250 0.5301 0.03004 0.02007 -0.0445 0.7087 1.0000
3.500 0.5552 0.03021 0.02032 -0.0426 0.6909 1.0000
3.750 0.5808 0.03022 0.02038 -0.0404 0.6742 1.0000
4.000 0.5991 0.03086 0.02109 -0.0387 0.6529 1.0000
4.250 0.6234 0.03088 0.02116 -0.0364 0.6348 1.0000
4.500 0.6491 0.03064 0.02100 -0.0339 0.6179 1.0000
4.750 0.6689 0.03115 0.02160 -0.0322 0.5964 1.0000
5.000 0.6940 0.03092 0.02143 -0.0297 0.5778 1.0000
5.250 0.7186 0.03075 0.02134 -0.0273 0.5588 1.0000
5.500 0.7409 0.03096 0.02164 -0.0253 0.5371 1.0000
5.750 0.7679 0.03043 0.02111 -0.0226 0.5183 1.0000
6.000 0.7889 0.03102 0.02181 -0.0210 0.4947 1.0000
6.250 0.8136 0.03100 0.02180 -0.0188 0.4732 1.0000
6.500 0.8369 0.03136 0.02225 -0.0170 0.4503 1.0000
6.750 0.8590 0.03197 0.02292 -0.0154 0.4268 1.0000
7.000 0.8849 0.03212 0.02299 -0.0134 0.4050 1.0000
7.250 0.9042 0.03331 0.02434 -0.0122 0.3810 1.0000
7.500 0.9263 0.03419 0.02525 -0.0107 0.3590 1.0000
7.750 0.9479 0.03519 0.02636 -0.0093 0.3369 1.0000
8.000 0.9673 0.03652 0.02780 -0.0080 0.3156 1.0000
8.250 0.9877 0.03780 0.02916 -0.0067 0.2951 1.0000
8.500 1.0070 0.03918 0.03060 -0.0053 0.2750 1.0000
8.750 1.0222 0.04113 0.03277 -0.0041 0.2562 1.0000
9.000 1.0465 0.04193 0.03338 -0.0026 0.2354 1.0000
9.250 1.0566 0.04455 0.03633 -0.0013 0.2193 1.0000
9.500 1.0657 0.04696 0.03904 0.0001 0.2026 1.0000
9.750 1.0744 0.04960 0.04188 0.0015 0.1879 1.0000
10.000 1.0806 0.05241 0.04487 0.0029 0.1745 1.0000
10.250 1.0852 0.05518 0.04780 0.0043 0.1620 1.0000
10.500 1.0937 0.05820 0.05088 0.0055 0.1512 1.0000
10.750 1.0705 0.06342 0.05650 0.0064 0.1498 1.0000
11.000 1.0431 0.06874 0.06203 0.0067 0.1502 1.0000
11.250 1.0139 0.07463 0.06801 0.0058 0.1514 1.0000
11.500 0.9867 0.08154 0.07495 0.0034 0.1527 1.0000
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Polar data table (+)
Polar graphs
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