MH 23 8% (mh23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.2 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh23-il-1000000-n5.txt Download as CSV file: xf-mh23-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5129 0.07807 0.07654 -0.0308 1.0000 0.0020
-8.750 -0.5204 0.07412 0.07262 -0.0336 1.0000 0.0022
-8.500 -0.5242 0.06611 0.06460 -0.0435 0.9879 0.0020
-8.250 -0.5189 0.05940 0.05778 -0.0508 0.9813 0.0022
-8.000 -0.5155 0.05360 0.05186 -0.0540 0.9739 0.0022
-7.750 -0.5118 0.04850 0.04660 -0.0551 0.9680 0.0023
-7.500 -0.5028 0.04609 0.04408 -0.0547 0.9630 0.0025
-7.250 -0.4961 0.04241 0.04024 -0.0537 0.9585 0.0027
-7.000 -0.4894 0.03825 0.03586 -0.0521 0.9547 0.0028
-6.750 -0.4795 0.03454 0.03194 -0.0504 0.9509 0.0030
-6.500 -0.4690 0.03073 0.02787 -0.0481 0.9472 0.0032
-6.250 -0.4578 0.02704 0.02387 -0.0456 0.9440 0.0032
-6.000 -0.4427 0.02411 0.02061 -0.0435 0.9412 0.0033
-5.750 -0.4250 0.02171 0.01794 -0.0417 0.9382 0.0035
-5.500 -0.4021 0.02073 0.01681 -0.0407 0.9358 0.0040
-4.750 -0.3386 0.01583 0.01119 -0.0365 0.9281 0.0042
-4.500 -0.3168 0.01366 0.00874 -0.0351 0.9247 0.0039
-4.250 -0.2932 0.01228 0.00719 -0.0340 0.9217 0.0038
-4.000 -0.2696 0.01118 0.00595 -0.0329 0.9188 0.0037
-3.750 -0.2465 0.01022 0.00486 -0.0317 0.9159 0.0035
-3.500 -0.2224 0.00953 0.00408 -0.0308 0.9124 0.0035
-3.250 -0.1983 0.00893 0.00335 -0.0299 0.9085 0.0034
-3.000 -0.1735 0.00848 0.00280 -0.0291 0.9049 0.0033
-2.750 -0.1480 0.00814 0.00238 -0.0285 0.9013 0.0033
-2.500 -0.1218 0.00787 0.00205 -0.0280 0.8969 0.0033
-2.250 -0.0954 0.00767 0.00178 -0.0276 0.8924 0.0034
-2.000 -0.0689 0.00750 0.00156 -0.0273 0.8877 0.0036
-1.750 -0.0420 0.00736 0.00139 -0.0270 0.8817 0.0053
-1.500 -0.0177 0.00691 0.00119 -0.0263 0.8759 0.0829
-1.250 0.0050 0.00627 0.00105 -0.0256 0.8677 0.2320
-1.000 0.0238 0.00534 0.00092 -0.0242 0.8581 0.4741
-0.750 0.0466 0.00494 0.00083 -0.0232 0.8457 0.5771
-0.500 0.0689 0.00461 0.00074 -0.0220 0.8280 0.6683
-0.250 0.0895 0.00429 0.00064 -0.0204 0.8032 0.7629
0.000 0.1103 0.00413 0.00063 -0.0186 0.7710 0.8456
0.250 0.1357 0.00418 0.00072 -0.0179 0.7347 0.9043
0.500 0.1657 0.00442 0.00085 -0.0182 0.6935 0.9343
0.750 0.1927 0.00467 0.00095 -0.0180 0.6522 0.9473
1.000 0.2164 0.00490 0.00102 -0.0171 0.6120 0.9560
1.250 0.2453 0.00516 0.00110 -0.0174 0.5683 0.9599
1.500 0.2714 0.00541 0.00119 -0.0171 0.5248 0.9650
1.750 0.2966 0.00566 0.00128 -0.0166 0.4837 0.9695
2.000 0.3300 0.00594 0.00140 -0.0181 0.4383 0.9718
2.250 0.3652 0.00625 0.00152 -0.0200 0.3929 0.9745
2.500 0.3974 0.00654 0.00165 -0.0212 0.3527 0.9781
2.750 0.4244 0.00682 0.00179 -0.0212 0.3141 0.9819
3.250 0.4891 0.00738 0.00207 -0.0238 0.2353 0.9839
3.500 0.5198 0.00766 0.00221 -0.0247 0.1990 0.9851
3.750 0.5498 0.00792 0.00236 -0.0255 0.1702 0.9863
4.000 0.5789 0.00818 0.00253 -0.0261 0.1435 0.9876
4.250 0.6066 0.00855 0.00273 -0.0264 0.1057 0.9890
4.500 0.6337 0.00893 0.00298 -0.0266 0.0741 0.9905
4.750 0.6587 0.00948 0.00329 -0.0265 0.0311 0.9920
5.000 0.6849 0.00980 0.00355 -0.0264 0.0192 0.9933
5.250 0.7127 0.01007 0.00379 -0.0267 0.0126 0.9942
5.500 0.7414 0.01034 0.00405 -0.0271 0.0085 0.9949
5.750 0.7689 0.01079 0.00445 -0.0274 0.0016 0.9957
6.000 0.7974 0.01109 0.00479 -0.0278 0.0013 0.9966
6.250 0.8253 0.01145 0.00525 -0.0281 0.0011 0.9975
6.500 0.8527 0.01181 0.00568 -0.0283 0.0010 0.9984
6.750 0.8798 0.01229 0.00625 -0.0284 0.0010 0.9992
7.000 0.9066 0.01280 0.00685 -0.0285 0.0009 1.0000
7.250 0.9261 0.01332 0.00747 -0.0270 0.0009 1.0000
7.500 0.9445 0.01390 0.00815 -0.0253 0.0009 1.0000
7.750 0.9612 0.01465 0.00902 -0.0232 0.0009 1.0000
8.000 0.9770 0.01546 0.00997 -0.0210 0.0009 1.0000
8.250 0.9920 0.01634 0.01099 -0.0187 0.0009 1.0000
8.500 1.0055 0.01736 0.01217 -0.0162 0.0009 1.0000
8.750 1.0176 0.01853 0.01352 -0.0134 0.0009 1.0000
9.000 1.0287 0.01980 0.01497 -0.0105 0.0009 1.0000
9.250 1.0367 0.02145 0.01686 -0.0071 0.0009 1.0000
9.500 1.0443 0.02309 0.01872 -0.0038 0.0009 1.0000
9.750 1.0483 0.02511 0.02106 -0.0001 0.0010 1.0000
10.000 1.0488 0.02738 0.02362 0.0040 0.0010 1.0000
10.250 1.0454 0.02984 0.02637 0.0084 0.0010 1.0000
10.500 1.0399 0.03191 0.02866 0.0129 0.0010 1.0000
10.750 1.0240 0.03447 0.03147 0.0186 0.0010 1.0000
11.000 1.0043 0.03765 0.03491 0.0235 0.0010 1.0000
11.250 0.9879 0.04075 0.03823 0.0268 0.0010 1.0000
11.500 0.9759 0.04367 0.04130 0.0287 0.0010 1.0000
11.750 0.9526 0.04838 0.04622 0.0293 0.0010 1.0000
12.000 0.9403 0.05252 0.05049 0.0281 0.0010 1.0000
12.250 0.9159 0.06005 0.05820 0.0233 0.0010 1.0000
12.500 0.9028 0.06760 0.06588 0.0173 0.0010 1.0000
12.750 0.8744 0.08164 0.08007 0.0075 0.0010 1.0000
13.000 0.8563 0.09185 0.09029 0.0026 0.0010 1.0000
13.250 0.8324 0.10247 0.10093 -0.0019 0.0010 1.0000
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Polar data table (+)
Polar graphs
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