MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 100,000 Max Cl/Cd: 49.08 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh43-il-100000-n5.txt Download as CSV file: xf-mh43-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 43 8.5%
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 -0.5235 0.09100 0.08631 -0.0048 1.0000 0.0159
-8.500 -0.5245 0.08625 0.08162 -0.0076 1.0000 0.0154
-8.250 -0.5270 0.08125 0.07670 -0.0108 1.0000 0.0149
-8.000 -0.5315 0.07599 0.07152 -0.0147 1.0000 0.0146
-7.750 -0.5372 0.06969 0.06526 -0.0206 1.0000 0.0143
-7.500 -0.5406 0.06140 0.05689 -0.0269 1.0000 0.0136
-7.250 -0.5417 0.05361 0.04885 -0.0308 1.0000 0.0130
-7.000 -0.5367 0.04786 0.04274 -0.0327 1.0000 0.0126
-6.750 -0.5266 0.04338 0.03786 -0.0335 1.0000 0.0123
-6.500 -0.5139 0.03932 0.03337 -0.0337 1.0000 0.0122
-6.250 -0.4985 0.03573 0.02934 -0.0335 1.0000 0.0122
-6.000 -0.4816 0.03225 0.02537 -0.0331 1.0000 0.0122
-5.750 -0.4632 0.02906 0.02172 -0.0324 1.0000 0.0124
-5.500 -0.4432 0.02639 0.01866 -0.0316 1.0000 0.0127
-5.250 -0.4229 0.02430 0.01630 -0.0307 1.0000 0.0135
-5.000 -0.4025 0.02300 0.01484 -0.0299 1.0000 0.0155
-4.750 -0.3829 0.02179 0.01342 -0.0286 1.0000 0.0182
-4.500 -0.3618 0.02050 0.01192 -0.0274 0.9976 0.0201
-4.250 -0.3272 0.01858 0.00976 -0.0290 0.9845 0.0232
-4.000 -0.2921 0.01729 0.00836 -0.0307 0.9719 0.0343
-3.750 -0.2582 0.01586 0.00707 -0.0321 0.9594 0.0722
-3.500 -0.2253 0.01478 0.00637 -0.0336 0.9471 0.1555
-3.250 -0.1932 0.01408 0.00594 -0.0348 0.9347 0.2427
-3.000 -0.1633 0.01341 0.00561 -0.0355 0.9222 0.3410
-2.750 -0.1353 0.01283 0.00535 -0.0355 0.9097 0.4468
-2.500 -0.1089 0.01233 0.00513 -0.0349 0.8976 0.5579
-2.250 -0.0838 0.01197 0.00503 -0.0336 0.8859 0.6619
-2.000 -0.0587 0.01174 0.00495 -0.0320 0.8743 0.7531
-1.750 -0.0300 0.01161 0.00487 -0.0312 0.8630 0.8307
-1.500 0.0078 0.01154 0.00470 -0.0323 0.8528 0.8944
-1.250 0.0515 0.01150 0.00449 -0.0349 0.8431 0.9426
-1.000 0.0983 0.01145 0.00426 -0.0385 0.8334 0.9790
-0.750 0.1381 0.01142 0.00407 -0.0411 0.8220 1.0000
-0.500 0.1607 0.01148 0.00397 -0.0401 0.8096 1.0000
-0.250 0.1837 0.01155 0.00391 -0.0392 0.7976 1.0000
0.000 0.2073 0.01163 0.00388 -0.0383 0.7860 1.0000
0.250 0.2309 0.01172 0.00386 -0.0374 0.7746 1.0000
0.500 0.2547 0.01181 0.00386 -0.0365 0.7634 1.0000
0.750 0.2787 0.01191 0.00387 -0.0356 0.7520 1.0000
1.000 0.3031 0.01201 0.00391 -0.0349 0.7399 1.0000
1.250 0.3277 0.01212 0.00396 -0.0342 0.7278 1.0000
1.500 0.3525 0.01223 0.00403 -0.0334 0.7154 1.0000
1.750 0.3774 0.01234 0.00412 -0.0327 0.7028 1.0000
2.000 0.4024 0.01245 0.00420 -0.0320 0.6899 1.0000
2.250 0.4276 0.01257 0.00430 -0.0314 0.6767 1.0000
2.500 0.4529 0.01269 0.00441 -0.0307 0.6630 1.0000
2.750 0.4782 0.01282 0.00458 -0.0301 0.6487 1.0000
3.000 0.5036 0.01295 0.00472 -0.0294 0.6337 1.0000
3.250 0.5290 0.01308 0.00486 -0.0287 0.6178 1.0000
3.500 0.5544 0.01322 0.00503 -0.0281 0.6004 1.0000
3.750 0.5798 0.01337 0.00522 -0.0275 0.5810 1.0000
4.000 0.6050 0.01353 0.00544 -0.0268 0.5607 1.0000
4.250 0.6301 0.01371 0.00566 -0.0261 0.5374 1.0000
4.500 0.6551 0.01392 0.00589 -0.0254 0.5114 1.0000
4.750 0.6797 0.01416 0.00614 -0.0247 0.4824 1.0000
5.000 0.7041 0.01446 0.00644 -0.0239 0.4487 1.0000
5.250 0.7279 0.01483 0.00684 -0.0232 0.4098 1.0000
5.500 0.7510 0.01531 0.00724 -0.0224 0.3657 1.0000
5.750 0.7734 0.01593 0.00772 -0.0216 0.3178 1.0000
6.000 0.7950 0.01669 0.00832 -0.0209 0.2668 1.0000
6.250 0.8162 0.01755 0.00903 -0.0201 0.2166 1.0000
6.500 0.8366 0.01854 0.00984 -0.0194 0.1695 1.0000
6.750 0.8566 0.01962 0.01076 -0.0187 0.1281 1.0000
7.000 0.8758 0.02082 0.01181 -0.0179 0.0936 1.0000
7.250 0.8947 0.02207 0.01302 -0.0170 0.0703 1.0000
7.500 0.9124 0.02347 0.01446 -0.0159 0.0530 1.0000
7.750 0.9290 0.02497 0.01600 -0.0148 0.0419 1.0000
8.000 0.9456 0.02652 0.01776 -0.0134 0.0352 1.0000
8.250 0.9607 0.02822 0.01955 -0.0121 0.0287 1.0000
8.500 0.9762 0.02992 0.02143 -0.0107 0.0241 1.0000
8.750 0.9872 0.03241 0.02397 -0.0092 0.0208 1.0000
9.000 1.0037 0.03401 0.02590 -0.0080 0.0171 1.0000
9.250 1.0164 0.03635 0.02848 -0.0066 0.0152 1.0000
9.500 1.0269 0.03882 0.03118 -0.0052 0.0142 1.0000
9.750 1.0327 0.04173 0.03430 -0.0038 0.0131 1.0000
10.000 1.0315 0.04568 0.03855 -0.0021 0.0123 1.0000
10.250 1.0306 0.04811 0.04133 -0.0002 0.0118 1.0000
10.500 1.0246 0.05119 0.04473 0.0013 0.0115 1.0000
10.750 1.0164 0.05452 0.04833 0.0020 0.0112 1.0000
11.000 1.0058 0.05815 0.05225 0.0017 0.0102 1.0000
11.250 0.9921 0.06279 0.05714 0.0005 0.0105 1.0000
11.500 0.9765 0.06808 0.06264 -0.0017 0.0108 1.0000
11.750 0.9601 0.07399 0.06875 -0.0049 0.0108 1.0000
12.000 0.9428 0.08070 0.07562 -0.0091 0.0111 1.0000
12.250 0.9240 0.08848 0.08356 -0.0143 0.0113 1.0000
12.500 0.9061 0.09686 0.09203 -0.0198 0.0117 1.0000
12.750 0.8886 0.10589 0.10112 -0.0255 0.0121 1.0000
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Polar data table (+)
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