MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 200,000 Max Cl/Cd: 66.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh43-il-200000.txt Download as CSV file: xf-mh43-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4468 0.08787 0.08485 -0.0073 1.0000 0.0431
-8.500 -0.4535 0.08293 0.07995 -0.0116 1.0000 0.0436
-8.250 -0.4587 0.07789 0.07495 -0.0155 1.0000 0.0438
-8.000 -0.4670 0.07235 0.06944 -0.0205 1.0000 0.0439
-7.750 -0.4794 0.06694 0.06400 -0.0252 1.0000 0.0439
-7.500 -0.4859 0.06174 0.05868 -0.0283 1.0000 0.0440
-7.250 -0.4898 0.05376 0.05080 -0.0292 1.0000 0.0453
-7.000 -0.4811 0.05023 0.04730 -0.0290 1.0000 0.0465
-6.750 -0.4744 0.04613 0.04316 -0.0300 1.0000 0.0478
-6.500 -0.4674 0.04154 0.03848 -0.0317 1.0000 0.0497
-6.250 -0.4592 0.03655 0.03329 -0.0336 1.0000 0.0527
-6.000 -0.4792 0.04301 0.03877 -0.0358 1.0000 0.0581
-5.750 -0.4616 0.03975 0.03558 -0.0357 1.0000 0.0601
-5.500 -0.4430 0.03021 0.02509 -0.0338 1.0000 0.0277
-5.250 -0.4216 0.02722 0.02134 -0.0314 1.0000 0.0212
-5.000 -0.4108 0.02357 0.01740 -0.0292 1.0000 0.0198
-4.750 -0.4015 0.02155 0.01508 -0.0263 1.0000 0.0193
-4.500 -0.3643 0.01895 0.01207 -0.0281 0.9938 0.0188
-4.250 -0.3249 0.01688 0.00969 -0.0302 0.9861 0.0192
-4.000 -0.2838 0.01529 0.00793 -0.0326 0.9797 0.0206
-3.750 -0.2462 0.01359 0.00617 -0.0347 0.9707 0.0283
-3.500 -0.2125 0.01148 0.00482 -0.0364 0.9603 0.1696
-3.250 -0.1781 0.01077 0.00446 -0.0381 0.9496 0.2745
-3.000 -0.1474 0.01019 0.00420 -0.0388 0.9378 0.3717
-2.750 -0.1229 0.00954 0.00404 -0.0381 0.9248 0.5124
-2.500 -0.1021 0.00903 0.00400 -0.0361 0.9119 0.6484
-2.250 -0.0817 0.00873 0.00399 -0.0336 0.8998 0.7535
-2.000 -0.0599 0.00859 0.00399 -0.0312 0.8879 0.8377
-1.750 -0.0297 0.00855 0.00395 -0.0305 0.8769 0.9027
-1.500 0.0129 0.00857 0.00382 -0.0328 0.8674 0.9463
-1.250 0.0615 0.00857 0.00366 -0.0366 0.8585 0.9744
-1.000 0.1134 0.00854 0.00346 -0.0414 0.8485 0.9955
-0.750 0.1416 0.00854 0.00332 -0.0417 0.8363 1.0000
-0.500 0.1628 0.00858 0.00323 -0.0404 0.8239 1.0000
-0.250 0.1848 0.00864 0.00317 -0.0392 0.8120 1.0000
0.000 0.2074 0.00870 0.00313 -0.0381 0.8005 1.0000
0.250 0.2305 0.00877 0.00310 -0.0371 0.7893 1.0000
0.500 0.2539 0.00885 0.00308 -0.0361 0.7783 1.0000
0.750 0.2780 0.00892 0.00307 -0.0352 0.7664 1.0000
1.000 0.3023 0.00900 0.00309 -0.0344 0.7544 1.0000
1.250 0.3270 0.00908 0.00311 -0.0337 0.7425 1.0000
1.500 0.3519 0.00916 0.00314 -0.0329 0.7307 1.0000
1.750 0.3770 0.00924 0.00319 -0.0322 0.7188 1.0000
2.000 0.4022 0.00933 0.00323 -0.0316 0.7066 1.0000
2.250 0.4277 0.00941 0.00328 -0.0309 0.6940 1.0000
2.500 0.4533 0.00950 0.00334 -0.0303 0.6807 1.0000
2.750 0.4790 0.00959 0.00344 -0.0297 0.6667 1.0000
3.000 0.5048 0.00967 0.00352 -0.0291 0.6519 1.0000
3.250 0.5307 0.00976 0.00360 -0.0286 0.6361 1.0000
3.500 0.5565 0.00985 0.00368 -0.0280 0.6195 1.0000
3.750 0.5823 0.00996 0.00380 -0.0274 0.6021 1.0000
4.000 0.6082 0.01005 0.00393 -0.0269 0.5814 1.0000
4.250 0.6339 0.01018 0.00405 -0.0263 0.5602 1.0000
4.500 0.6595 0.01033 0.00418 -0.0257 0.5355 1.0000
4.750 0.6849 0.01051 0.00435 -0.0251 0.5077 1.0000
5.000 0.7102 0.01073 0.00456 -0.0246 0.4749 1.0000
5.250 0.7349 0.01102 0.00485 -0.0240 0.4365 1.0000
5.500 0.7589 0.01143 0.00515 -0.0233 0.3907 1.0000
5.750 0.7822 0.01197 0.00553 -0.0227 0.3377 1.0000
6.000 0.8044 0.01270 0.00602 -0.0221 0.2785 1.0000
6.250 0.8260 0.01355 0.00662 -0.0214 0.2165 1.0000
6.500 0.8467 0.01458 0.00736 -0.0208 0.1585 1.0000
6.750 0.8668 0.01573 0.00825 -0.0201 0.1084 1.0000
7.000 0.8859 0.01706 0.00940 -0.0191 0.0724 1.0000
7.250 0.9030 0.01872 0.01097 -0.0178 0.0530 1.0000
7.500 0.9213 0.02015 0.01251 -0.0166 0.0407 1.0000
7.750 0.9375 0.02194 0.01432 -0.0152 0.0309 1.0000
8.000 0.9563 0.02320 0.01567 -0.0141 0.0223 1.0000
8.250 0.9739 0.02493 0.01756 -0.0128 0.0173 1.0000
8.500 0.9913 0.02677 0.01954 -0.0115 0.0150 1.0000
8.750 1.0078 0.02906 0.02199 -0.0102 0.0140 1.0000
9.000 1.0218 0.03238 0.02559 -0.0087 0.0132 1.0000
9.250 1.0331 0.03610 0.02968 -0.0072 0.0130 1.0000
9.500 1.0426 0.03929 0.03322 -0.0056 0.0130 1.0000
9.750 1.0476 0.04261 0.03691 -0.0038 0.0131 1.0000
10.000 1.0492 0.04572 0.04037 -0.0019 0.0133 1.0000
10.250 1.0439 0.04893 0.04395 0.0004 0.0137 1.0000
10.500 1.0277 0.05285 0.04823 0.0029 0.0144 1.0000
10.750 1.0073 0.05723 0.05292 0.0038 0.0148 1.0000
11.000 0.9847 0.06231 0.05825 0.0029 0.0150 1.0000
11.250 0.9624 0.06814 0.06432 0.0004 0.0154 1.0000
11.500 0.9408 0.07466 0.07102 -0.0036 0.0157 1.0000
11.750 0.9202 0.08198 0.07849 -0.0087 0.0158 1.0000
12.000 0.8986 0.09083 0.08747 -0.0152 0.0160 1.0000
12.250 0.8731 0.10272 0.09945 -0.0236 0.0163 1.0000
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Polar data table (+)
Polar graphs
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