MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 100,000 Max Cl/Cd: 46.58 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh60-il-100000-n5.txt Download as CSV file: xf-mh60-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5626 0.09259 0.08812 0.0033 1.0000 0.0165
-9.250 -0.5645 0.08729 0.08288 0.0002 1.0000 0.0163
-9.000 -0.5679 0.08156 0.07720 -0.0035 1.0000 0.0161
-8.750 -0.5718 0.07558 0.07128 -0.0080 1.0000 0.0157
-8.500 -0.5828 0.06670 0.06242 -0.0164 1.0000 0.0154
-8.250 -0.5971 0.06023 0.05583 -0.0214 1.0000 0.0153
-8.000 -0.6041 0.05455 0.04992 -0.0245 1.0000 0.0151
-7.750 -0.6052 0.04934 0.04440 -0.0263 1.0000 0.0148
-7.500 -0.6011 0.04446 0.03911 -0.0272 1.0000 0.0147
-7.250 -0.5916 0.04013 0.03432 -0.0276 1.0000 0.0146
-7.000 -0.5778 0.03629 0.02999 -0.0276 1.0000 0.0147
-6.750 -0.5606 0.03308 0.02631 -0.0273 1.0000 0.0148
-6.500 -0.5414 0.03029 0.02308 -0.0268 1.0000 0.0152
-6.250 -0.5187 0.02812 0.02045 -0.0266 0.9894 0.0163
-6.000 -0.4874 0.02588 0.01793 -0.0281 0.9694 0.0181
-5.750 -0.4562 0.02434 0.01615 -0.0293 0.9548 0.0202
-5.500 -0.4266 0.02273 0.01431 -0.0297 0.9420 0.0216
-5.250 -0.3998 0.02140 0.01276 -0.0294 0.9295 0.0235
-5.000 -0.3765 0.02017 0.01146 -0.0287 0.9171 0.0273
-4.750 -0.3527 0.01933 0.01045 -0.0278 0.9054 0.0336
-4.500 -0.3302 0.01832 0.00936 -0.0267 0.8944 0.0449
-4.250 -0.3085 0.01724 0.00838 -0.0255 0.8843 0.0733
-4.000 -0.2871 0.01620 0.00774 -0.0245 0.8743 0.1492
-3.750 -0.2643 0.01557 0.00738 -0.0237 0.8642 0.2267
-3.500 -0.2414 0.01511 0.00713 -0.0227 0.8549 0.2972
-3.250 -0.2184 0.01474 0.00690 -0.0216 0.8459 0.3592
-3.000 -0.1944 0.01441 0.00666 -0.0207 0.8362 0.4142
-2.750 -0.1707 0.01411 0.00644 -0.0196 0.8275 0.4673
-2.500 -0.1466 0.01383 0.00625 -0.0184 0.8185 0.5209
-2.250 -0.1221 0.01355 0.00609 -0.0174 0.8092 0.5776
-2.000 -0.0976 0.01328 0.00592 -0.0161 0.8009 0.6389
-1.750 -0.0723 0.01302 0.00581 -0.0150 0.7914 0.7064
-1.500 -0.0440 0.01280 0.00573 -0.0142 0.7824 0.7808
-1.250 -0.0063 0.01265 0.00561 -0.0151 0.7743 0.8562
-1.000 0.0410 0.01259 0.00546 -0.0183 0.7641 0.9159
-0.750 0.0859 0.01257 0.00529 -0.0214 0.7543 0.9574
-0.500 0.1294 0.01253 0.00508 -0.0243 0.7449 0.9883
-0.250 0.1623 0.01253 0.00494 -0.0254 0.7336 1.0000
0.000 0.1860 0.01256 0.00485 -0.0247 0.7225 1.0000
0.250 0.2098 0.01259 0.00477 -0.0238 0.7116 1.0000
0.500 0.2336 0.01263 0.00468 -0.0229 0.7008 1.0000
0.750 0.2579 0.01267 0.00463 -0.0221 0.6892 1.0000
1.000 0.2826 0.01273 0.00461 -0.0214 0.6766 1.0000
1.250 0.3074 0.01279 0.00461 -0.0207 0.6639 1.0000
1.500 0.3323 0.01286 0.00460 -0.0200 0.6507 1.0000
1.750 0.3572 0.01293 0.00461 -0.0193 0.6372 1.0000
2.000 0.3823 0.01301 0.00463 -0.0186 0.6230 1.0000
2.250 0.4074 0.01310 0.00468 -0.0179 0.6082 1.0000
2.500 0.4326 0.01320 0.00472 -0.0173 0.5929 1.0000
2.750 0.4578 0.01331 0.00477 -0.0166 0.5770 1.0000
3.000 0.4830 0.01343 0.00483 -0.0159 0.5606 1.0000
3.250 0.5085 0.01359 0.00498 -0.0154 0.5424 1.0000
3.500 0.5339 0.01376 0.00511 -0.0148 0.5241 1.0000
3.750 0.5591 0.01395 0.00524 -0.0142 0.5057 1.0000
4.000 0.5844 0.01417 0.00542 -0.0137 0.4865 1.0000
4.250 0.6097 0.01441 0.00566 -0.0132 0.4668 1.0000
4.500 0.6347 0.01469 0.00587 -0.0126 0.4476 1.0000
4.750 0.6599 0.01498 0.00616 -0.0122 0.4273 1.0000
5.000 0.6848 0.01531 0.00645 -0.0117 0.4075 1.0000
5.250 0.7096 0.01566 0.00681 -0.0112 0.3879 1.0000
5.500 0.7343 0.01604 0.00719 -0.0108 0.3678 1.0000
5.750 0.7586 0.01645 0.00757 -0.0103 0.3488 1.0000
6.000 0.7830 0.01687 0.00802 -0.0099 0.3288 1.0000
6.250 0.8070 0.01733 0.00852 -0.0094 0.3096 1.0000
6.500 0.8306 0.01783 0.00902 -0.0089 0.2905 1.0000
6.750 0.8541 0.01835 0.00958 -0.0084 0.2713 1.0000
7.000 0.8770 0.01892 0.01016 -0.0079 0.2525 1.0000
7.250 0.8994 0.01953 0.01078 -0.0073 0.2347 1.0000
7.500 0.9217 0.02017 0.01151 -0.0068 0.2167 1.0000
7.750 0.9433 0.02085 0.01224 -0.0062 0.1998 1.0000
8.000 0.9642 0.02160 0.01301 -0.0055 0.1835 1.0000
8.250 0.9843 0.02240 0.01384 -0.0048 0.1682 1.0000
8.500 1.0037 0.02325 0.01473 -0.0041 0.1536 1.0000
8.750 1.0223 0.02415 0.01569 -0.0033 0.1397 1.0000
9.250 1.0563 0.02613 0.01783 -0.0015 0.1128 1.0000
9.500 1.0716 0.02723 0.01900 -0.0005 0.1001 1.0000
9.750 1.0856 0.02839 0.02027 0.0005 0.0884 1.0000
10.000 1.0977 0.02966 0.02163 0.0017 0.0771 1.0000
10.250 1.1075 0.03105 0.02312 0.0030 0.0673 1.0000
10.500 1.1125 0.03264 0.02473 0.0047 0.0600 1.0000
10.750 1.1154 0.03430 0.02651 0.0063 0.0535 1.0000
11.000 1.1153 0.03636 0.02863 0.0077 0.0491 1.0000
11.250 1.1172 0.03845 0.03087 0.0087 0.0441 1.0000
11.500 1.1143 0.04102 0.03352 0.0093 0.0406 1.0000
11.750 1.1144 0.04358 0.03625 0.0097 0.0373 1.0000
12.000 1.1129 0.04640 0.03923 0.0099 0.0346 1.0000
12.250 1.1091 0.04957 0.04251 0.0095 0.0323 1.0000
12.500 1.1020 0.05323 0.04623 0.0088 0.0306 1.0000
12.750 1.0983 0.05680 0.04999 0.0082 0.0289 1.0000
13.000 1.0931 0.06071 0.05411 0.0069 0.0269 1.0000
13.250 1.0866 0.06494 0.05851 0.0054 0.0256 1.0000
13.500 1.0789 0.06948 0.06319 0.0036 0.0246 1.0000
13.750 1.0703 0.07435 0.06819 0.0015 0.0238 1.0000
14.000 1.0599 0.07963 0.07358 -0.0011 0.0230 1.0000
14.250 1.0508 0.08491 0.07896 -0.0035 0.0224 1.0000
14.500 1.0390 0.09097 0.08514 -0.0065 0.0217 1.0000
14.750 1.0270 0.09750 0.09187 -0.0099 0.0214 1.0000
15.000 1.0125 0.10485 0.09941 -0.0140 0.0210 1.0000
15.250 0.9977 0.11249 0.10721 -0.0182 0.0209 1.0000
15.500 0.9822 0.12065 0.11552 -0.0227 0.0210 1.0000
15.750 0.9658 0.12933 0.12433 -0.0275 0.0212 1.0000
16.000 0.9486 0.13867 0.13377 -0.0326 0.0214 1.0000
16.250 0.9290 0.14927 0.14446 -0.0384 0.0217 1.0000
16.500 0.9089 0.16078 0.15599 -0.0444 0.0219 1.0000
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