MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 100,000 Max Cl/Cd: 45.17 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh64-il-100000-n5.txt Download as CSV file: xf-mh64-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5646 0.08986 0.08528 0.0040 1.0000 0.0150
-8.500 -0.5664 0.08483 0.08030 0.0009 1.0000 0.0147
-8.250 -0.5698 0.07943 0.07498 -0.0028 1.0000 0.0144
-8.000 -0.5750 0.07369 0.06930 -0.0076 1.0000 0.0141
-7.750 -0.5797 0.06635 0.06196 -0.0146 1.0000 0.0138
-7.500 -0.5819 0.05929 0.05483 -0.0196 1.0000 0.0134
-7.250 -0.5817 0.05287 0.04816 -0.0230 1.0000 0.0130
-7.000 -0.5772 0.04698 0.04191 -0.0251 1.0000 0.0127
-6.750 -0.5677 0.04172 0.03616 -0.0261 1.0000 0.0124
-6.500 -0.5538 0.03718 0.03100 -0.0263 1.0000 0.0122
-6.250 -0.5361 0.03350 0.02680 -0.0261 1.0000 0.0121
-6.000 -0.5159 0.03038 0.02320 -0.0257 1.0000 0.0122
-5.750 -0.4939 0.02774 0.02014 -0.0252 1.0000 0.0123
-5.500 -0.4707 0.02550 0.01755 -0.0246 1.0000 0.0127
-5.250 -0.4470 0.02382 0.01561 -0.0241 1.0000 0.0140
-5.000 -0.4230 0.02246 0.01403 -0.0235 1.0000 0.0165
-4.750 -0.3993 0.02126 0.01261 -0.0227 1.0000 0.0182
-4.500 -0.3799 0.01952 0.01080 -0.0214 1.0000 0.0198
-4.250 -0.3621 0.01836 0.00956 -0.0199 1.0000 0.0226
-4.000 -0.3307 0.01724 0.00821 -0.0209 0.9871 0.0302
-3.750 -0.2969 0.01560 0.00679 -0.0224 0.9742 0.0736
-3.500 -0.2650 0.01422 0.00618 -0.0241 0.9620 0.2274
-3.250 -0.2325 0.01358 0.00591 -0.0254 0.9500 0.3318
-3.000 -0.2010 0.01316 0.00565 -0.0261 0.9380 0.4068
-2.750 -0.1709 0.01283 0.00543 -0.0264 0.9260 0.4699
-2.500 -0.1426 0.01254 0.00519 -0.0261 0.9139 0.5307
-2.250 -0.1158 0.01228 0.00504 -0.0255 0.9016 0.5930
-2.000 -0.0906 0.01203 0.00492 -0.0243 0.8892 0.6595
-1.750 -0.0655 0.01179 0.00483 -0.0230 0.8771 0.7329
-1.500 -0.0363 0.01159 0.00475 -0.0222 0.8656 0.8140
-1.250 0.0061 0.01146 0.00459 -0.0242 0.8552 0.8942
-1.000 0.0525 0.01138 0.00439 -0.0274 0.8442 0.9541
-0.750 0.0975 0.01133 0.00417 -0.0307 0.8326 0.9955
-0.500 0.1223 0.01138 0.00404 -0.0301 0.8191 1.0000
-0.250 0.1450 0.01143 0.00397 -0.0289 0.8055 1.0000
0.000 0.1680 0.01150 0.00391 -0.0278 0.7919 1.0000
0.250 0.1914 0.01156 0.00387 -0.0267 0.7782 1.0000
0.500 0.2152 0.01163 0.00384 -0.0258 0.7642 1.0000
0.750 0.2393 0.01171 0.00383 -0.0248 0.7497 1.0000
1.000 0.2637 0.01178 0.00383 -0.0239 0.7347 1.0000
1.250 0.2883 0.01186 0.00384 -0.0231 0.7191 1.0000
1.500 0.3130 0.01195 0.00387 -0.0223 0.7030 1.0000
1.750 0.3379 0.01203 0.00391 -0.0214 0.6864 1.0000
2.000 0.3627 0.01212 0.00393 -0.0206 0.6694 1.0000
2.250 0.3881 0.01223 0.00401 -0.0199 0.6499 1.0000
2.500 0.4133 0.01234 0.00406 -0.0191 0.6303 1.0000
2.750 0.4387 0.01246 0.00420 -0.0185 0.6087 1.0000
3.000 0.4640 0.01261 0.00429 -0.0177 0.5864 1.0000
3.250 0.4894 0.01278 0.00442 -0.0171 0.5622 1.0000
3.500 0.5147 0.01297 0.00457 -0.0164 0.5365 1.0000
3.750 0.5401 0.01320 0.00479 -0.0158 0.5096 1.0000
4.000 0.5653 0.01347 0.00500 -0.0152 0.4820 1.0000
4.250 0.5905 0.01378 0.00525 -0.0146 0.4539 1.0000
4.500 0.6155 0.01412 0.00555 -0.0141 0.4256 1.0000
4.750 0.6405 0.01450 0.00588 -0.0136 0.3973 1.0000
5.000 0.6654 0.01491 0.00632 -0.0131 0.3686 1.0000
5.250 0.6902 0.01535 0.00675 -0.0127 0.3398 1.0000
5.500 0.7148 0.01583 0.00721 -0.0122 0.3111 1.0000
5.750 0.7390 0.01636 0.00772 -0.0118 0.2819 1.0000
6.000 0.7631 0.01693 0.00828 -0.0113 0.2534 1.0000
6.250 0.7867 0.01755 0.00890 -0.0109 0.2251 1.0000
6.500 0.8100 0.01824 0.00957 -0.0104 0.1976 1.0000
6.750 0.8329 0.01898 0.01039 -0.0099 0.1713 1.0000
7.000 0.8553 0.01980 0.01121 -0.0094 0.1457 1.0000
7.250 0.8771 0.02070 0.01210 -0.0089 0.1210 1.0000
7.500 0.8981 0.02171 0.01311 -0.0083 0.0984 1.0000
7.750 0.9180 0.02288 0.01423 -0.0077 0.0757 1.0000
8.000 0.9372 0.02416 0.01557 -0.0069 0.0574 1.0000
8.250 0.9547 0.02563 0.01708 -0.0061 0.0436 1.0000
8.500 0.9696 0.02747 0.01901 -0.0048 0.0358 1.0000
8.750 0.9829 0.02932 0.02091 -0.0038 0.0283 1.0000
9.000 0.9974 0.03117 0.02303 -0.0024 0.0242 1.0000
9.250 1.0094 0.03301 0.02499 -0.0013 0.0202 1.0000
9.500 1.0180 0.03536 0.02751 0.0001 0.0176 1.0000
9.750 1.0275 0.03775 0.03030 0.0016 0.0159 1.0000
10.000 1.0341 0.04041 0.03324 0.0031 0.0148 1.0000
10.250 1.0363 0.04308 0.03617 0.0046 0.0138 1.0000
10.500 1.0345 0.04566 0.03896 0.0061 0.0131 1.0000
10.750 1.0305 0.04839 0.04187 0.0069 0.0126 1.0000
11.000 1.0235 0.05150 0.04513 0.0070 0.0119 1.0000
11.250 1.0146 0.05535 0.04918 0.0064 0.0116 1.0000
12.000 0.9713 0.07148 0.06589 -0.0011 0.0110 1.0000
12.750 0.9245 0.09401 0.08915 -0.0158 0.0123 1.0000
13.000 0.8847 0.10964 0.10500 -0.0255 0.0141 1.0000
13.250 0.8590 0.12230 0.11760 -0.0325 0.0151 1.0000
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Polar data table (+)
Polar graphs
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