MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 200,000 Max Cl/Cd: 59.5 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh64-il-200000.txt Download as CSV file: xf-mh64-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 64 8.59%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5658 0.11267 0.10933 0.0173 1.0000 0.0365
-9.500 -0.5650 0.10826 0.10496 0.0142 1.0000 0.0381
-9.250 -0.5668 0.10374 0.10050 0.0093 1.0000 0.0394
-9.000 -0.4946 0.09153 0.08860 0.0036 1.0000 0.0414
-8.750 -0.4867 0.08797 0.08505 0.0039 1.0000 0.0426
-8.500 -0.4834 0.08398 0.08108 0.0030 1.0000 0.0437
-8.250 -0.4827 0.07957 0.07669 0.0013 1.0000 0.0448
-8.000 -0.4847 0.07487 0.07203 -0.0008 1.0000 0.0459
-7.750 -0.4894 0.06982 0.06701 -0.0036 1.0000 0.0470
-7.500 -0.4983 0.06443 0.06168 -0.0074 1.0000 0.0479
-7.250 -0.5105 0.05815 0.05540 -0.0134 1.0000 0.0482
-7.000 -0.5170 0.05089 0.04804 -0.0195 1.0000 0.0496
-6.750 -0.5252 0.04494 0.04138 -0.0255 1.0000 0.0528
-6.500 -0.5195 0.03694 0.03352 -0.0267 1.0000 0.0549
-6.250 -0.5034 0.03360 0.03020 -0.0271 1.0000 0.0572
-6.000 -0.4884 0.02963 0.02600 -0.0281 1.0000 0.0616
-5.750 -0.4750 0.02507 0.02110 -0.0293 1.0000 0.0689
-5.500 -0.4741 0.02749 0.02184 -0.0260 1.0000 0.0243
-5.250 -0.4496 0.02370 0.01723 -0.0244 1.0000 0.0194
-5.000 -0.4246 0.02268 0.01601 -0.0237 1.0000 0.0186
-4.750 -0.4062 0.02054 0.01364 -0.0222 1.0000 0.0181
-4.500 -0.3929 0.01886 0.01177 -0.0198 1.0000 0.0179
-4.250 -0.3658 0.01722 0.00997 -0.0198 0.9959 0.0182
-4.000 -0.3279 0.01521 0.00781 -0.0218 0.9881 0.0190
-3.750 -0.2879 0.01364 0.00615 -0.0244 0.9812 0.0240
-3.500 -0.2549 0.01117 0.00461 -0.0261 0.9712 0.2064
-3.250 -0.2206 0.01046 0.00444 -0.0279 0.9609 0.3465
-3.000 -0.1880 0.01008 0.00428 -0.0288 0.9501 0.4248
-2.750 -0.1602 0.00975 0.00418 -0.0286 0.9383 0.5033
-2.500 -0.1361 0.00946 0.00407 -0.0274 0.9260 0.5739
-2.250 -0.1146 0.00919 0.00401 -0.0256 0.9137 0.6471
-2.000 -0.0944 0.00891 0.00397 -0.0232 0.9016 0.7263
-1.750 -0.0729 0.00866 0.00395 -0.0209 0.8898 0.8148
-1.500 -0.0353 0.00852 0.00390 -0.0217 0.8799 0.9049
-1.250 0.0168 0.00849 0.00373 -0.0259 0.8711 0.9614
-1.000 0.0680 0.00845 0.00354 -0.0304 0.8613 0.9951
-0.750 0.0949 0.00846 0.00340 -0.0302 0.8485 1.0000
-0.500 0.1163 0.00849 0.00330 -0.0288 0.8355 1.0000
-0.250 0.1387 0.00853 0.00322 -0.0276 0.8227 1.0000
0.000 0.1616 0.00857 0.00316 -0.0264 0.8098 1.0000
0.250 0.1850 0.00862 0.00311 -0.0253 0.7968 1.0000
0.500 0.2088 0.00866 0.00306 -0.0242 0.7836 1.0000
0.750 0.2330 0.00871 0.00302 -0.0232 0.7702 1.0000
1.000 0.2574 0.00876 0.00299 -0.0223 0.7563 1.0000
1.250 0.2821 0.00880 0.00297 -0.0214 0.7419 1.0000
1.500 0.3071 0.00885 0.00295 -0.0205 0.7269 1.0000
1.750 0.3322 0.00891 0.00294 -0.0197 0.7114 1.0000
2.000 0.3577 0.00896 0.00294 -0.0190 0.6943 1.0000
2.250 0.3835 0.00902 0.00296 -0.0184 0.6756 1.0000
2.500 0.4091 0.00910 0.00296 -0.0177 0.6569 1.0000
2.750 0.4351 0.00918 0.00303 -0.0171 0.6352 1.0000
3.000 0.4609 0.00929 0.00307 -0.0165 0.6131 1.0000
3.250 0.4868 0.00942 0.00313 -0.0159 0.5887 1.0000
3.500 0.5128 0.00958 0.00323 -0.0154 0.5625 1.0000
3.750 0.5388 0.00977 0.00338 -0.0149 0.5351 1.0000
4.000 0.5647 0.01000 0.00353 -0.0144 0.5068 1.0000
4.250 0.5906 0.01027 0.00373 -0.0140 0.4776 1.0000
4.500 0.6164 0.01056 0.00395 -0.0136 0.4475 1.0000
4.750 0.6421 0.01089 0.00422 -0.0133 0.4172 1.0000
5.000 0.6676 0.01126 0.00455 -0.0129 0.3866 1.0000
5.250 0.6929 0.01166 0.00487 -0.0126 0.3560 1.0000
5.500 0.7182 0.01207 0.00524 -0.0122 0.3240 1.0000
5.750 0.7432 0.01254 0.00564 -0.0119 0.2918 1.0000
6.000 0.7678 0.01306 0.00608 -0.0116 0.2596 1.0000
6.250 0.7923 0.01361 0.00658 -0.0113 0.2272 1.0000
6.500 0.8163 0.01424 0.00712 -0.0109 0.1966 1.0000
6.750 0.8399 0.01493 0.00779 -0.0105 0.1678 1.0000
7.000 0.8631 0.01567 0.00845 -0.0101 0.1396 1.0000
7.250 0.8860 0.01646 0.00920 -0.0097 0.1115 1.0000
7.500 0.9079 0.01741 0.01009 -0.0092 0.0829 1.0000
7.750 0.9274 0.01882 0.01142 -0.0083 0.0582 1.0000
8.000 0.9456 0.02034 0.01288 -0.0073 0.0410 1.0000
8.250 0.9628 0.02196 0.01454 -0.0062 0.0295 1.0000
8.500 0.9803 0.02356 0.01628 -0.0050 0.0223 1.0000
8.750 0.9930 0.02595 0.01876 -0.0036 0.0177 1.0000
9.000 1.0095 0.02793 0.02095 -0.0022 0.0156 1.0000
9.250 1.0247 0.03019 0.02344 -0.0008 0.0144 1.0000
9.500 1.0384 0.03270 0.02627 0.0006 0.0138 1.0000
9.750 1.0493 0.03545 0.02932 0.0021 0.0134 1.0000
10.000 1.0559 0.03861 0.03282 0.0037 0.0133 1.0000
10.250 1.0567 0.04206 0.03664 0.0054 0.0133 1.0000
10.500 1.0507 0.04554 0.04046 0.0075 0.0135 1.0000
10.750 1.0374 0.04907 0.04429 0.0093 0.0137 1.0000
11.000 1.0211 0.05311 0.04860 0.0098 0.0139 1.0000
11.250 1.0038 0.05767 0.05341 0.0088 0.0141 1.0000
11.500 0.9863 0.06279 0.05874 0.0066 0.0141 1.0000
11.750 0.9655 0.06917 0.06533 0.0028 0.0144 1.0000
12.000 0.9456 0.07629 0.07263 -0.0022 0.0145 1.0000
12.250 0.9246 0.08464 0.08113 -0.0084 0.0147 1.0000
12.500 0.9039 0.09395 0.09057 -0.0151 0.0150 1.0000
12.750 0.8795 0.10535 0.10199 -0.0227 0.0154 1.0000
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Polar data table (+)
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