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MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 201 13.08% (mh201-il)
Reynolds number: 50,000
Max Cl/Cd: 33.95 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh201-il-50000.txt
Download as CSV file: xf-mh201-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 201  13.08%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3774   0.10865   0.10218  -0.0274   1.0000   0.2965
  -8.500  -0.3557   0.10407   0.09760  -0.0257   1.0000   0.3050
  -8.250  -0.3690   0.10212   0.09579  -0.0240   1.0000   0.3155
  -8.000  -0.3649   0.09930   0.09302  -0.0223   1.0000   0.3227
  -7.500  -0.3815   0.09455   0.08849  -0.0182   1.0000   0.3346
  -7.250  -0.3929   0.09231   0.08636  -0.0160   1.0000   0.3367
  -7.000  -0.4094   0.09015   0.08432  -0.0138   1.0000   0.3357
  -6.750  -0.5694   0.07122   0.06533  -0.0360   1.0000   0.1357
  -6.500  -0.5815   0.06519   0.05898  -0.0373   1.0000   0.1211
  -6.250  -0.5850   0.05909   0.05232  -0.0384   1.0000   0.1093
  -6.000  -0.5780   0.05433   0.04717  -0.0386   1.0000   0.1032
  -5.750  -0.5648   0.04971   0.04165  -0.0392   1.0000   0.0970
  -5.500  -0.5477   0.04625   0.03774  -0.0391   1.0000   0.0967
  -5.250  -0.5275   0.04317   0.03416  -0.0390   1.0000   0.0970
  -5.000  -0.5048   0.04047   0.03086  -0.0387   1.0000   0.0981
  -4.750  -0.4821   0.03762   0.02774  -0.0383   1.0000   0.0996
  -4.500  -0.4599   0.03554   0.02555  -0.0375   1.0000   0.1032
  -4.250  -0.4366   0.03394   0.02361  -0.0367   1.0000   0.1109
  -4.000  -0.4148   0.03226   0.02193  -0.0354   1.0000   0.1205
  -3.750  -0.3934   0.03088   0.02056  -0.0339   1.0000   0.1374
  -3.500  -0.3727   0.02946   0.01933  -0.0322   1.0000   0.1681
  -3.250  -0.3491   0.02593   0.01744  -0.0319   1.0000   0.3385
  -3.000  -0.3614   0.02568   0.01931  -0.0198   1.0000   0.6750
  -2.750  -0.3688   0.02694   0.02052  -0.0098   1.0000   0.7579
  -2.500  -0.3783   0.02768   0.02120   0.0003   1.0000   0.8152
  -2.250  -0.3866   0.02794   0.02140   0.0101   1.0000   0.8664
  -2.000  -0.1896   0.03080   0.02288  -0.0134   1.0000   0.9842
  -1.750  -0.1344   0.03071   0.02237  -0.0213   1.0000   1.0000
  -1.500  -0.1374   0.03029   0.02184  -0.0186   1.0000   1.0000
  -1.250  -0.1399   0.02992   0.02136  -0.0159   1.0000   1.0000
  -1.000  -0.1418   0.02957   0.02089  -0.0132   1.0000   1.0000
  -0.750  -0.1431   0.02925   0.02047  -0.0105   1.0000   1.0000
  -0.500  -0.1436   0.02895   0.02008  -0.0079   1.0000   1.0000
  -0.250  -0.1428   0.02870   0.01973  -0.0055   1.0000   1.0000
   0.000  -0.1387   0.02855   0.01948  -0.0036   1.0000   1.0000
   0.250  -0.1290   0.02861   0.01941  -0.0027   1.0000   1.0000
   0.500  -0.1148   0.02887   0.01953  -0.0027   1.0000   1.0000
   0.750  -0.0975   0.02929   0.01983  -0.0031   1.0000   1.0000
   1.000  -0.0785   0.02985   0.02026  -0.0039   1.0000   1.0000
   1.250  -0.0350   0.03141   0.02166  -0.0092   0.9889   1.0000
   1.500   0.0213   0.03339   0.02346  -0.0164   0.9703   1.0000
   1.750   0.0629   0.03461   0.02458  -0.0209   0.9533   1.0000
   2.000   0.1051   0.03586   0.02573  -0.0253   0.9366   1.0000
   2.250   0.1474   0.03708   0.02688  -0.0295   0.9199   1.0000
   2.500   0.1894   0.03825   0.02799  -0.0335   0.9032   1.0000
   2.750   0.2323   0.03939   0.02910  -0.0374   0.8865   1.0000
   3.000   0.2685   0.04034   0.03003  -0.0401   0.8691   1.0000
   3.250   0.3013   0.04121   0.03090  -0.0422   0.8512   1.0000
   3.500   0.3359   0.04208   0.03178  -0.0444   0.8331   1.0000
   3.750   0.3722   0.04292   0.03266  -0.0467   0.8151   1.0000
   4.000   0.4113   0.04365   0.03344  -0.0491   0.7970   1.0000
   4.250   0.4526   0.04425   0.03409  -0.0515   0.7793   1.0000
   4.500   0.4958   0.04468   0.03462  -0.0538   0.7621   1.0000
   4.750   0.5188   0.04540   0.03540  -0.0538   0.7416   1.0000
   5.000   0.5523   0.04580   0.03589  -0.0548   0.7223   1.0000
   5.250   0.5926   0.04585   0.03606  -0.0560   0.7038   1.0000
   5.500   0.6384   0.04541   0.03578  -0.0574   0.6861   1.0000
   5.750   0.6882   0.04442   0.03496  -0.0586   0.6692   1.0000
   6.000   0.7051   0.04513   0.03579  -0.0574   0.6462   1.0000
   6.250   0.7539   0.04363   0.03447  -0.0578   0.6282   1.0000
   6.500   0.8161   0.04073   0.03183  -0.0584   0.6114   1.0000
   6.750   0.9126   0.03578   0.02720  -0.0621   0.5925   1.0000
   7.000   0.9550   0.03439   0.02595  -0.0618   0.5651   1.0000
   7.250   1.0102   0.03253   0.02413  -0.0628   0.5337   1.0000
   7.500   1.0559   0.03165   0.02318  -0.0633   0.4993   1.0000
   7.750   1.0819   0.03200   0.02347  -0.0621   0.4660   1.0000
   8.000   1.1073   0.03262   0.02402  -0.0610   0.4336   1.0000
   8.250   1.1315   0.03349   0.02478  -0.0600   0.4028   1.0000
   8.500   1.1559   0.03453   0.02570  -0.0591   0.3738   1.0000
   8.750   1.1781   0.03579   0.02687  -0.0581   0.3471   1.0000
   9.000   1.1937   0.03737   0.02854  -0.0564   0.3240   1.0000
   9.250   1.2174   0.03886   0.02993  -0.0557   0.3014   1.0000
   9.500   1.2356   0.04064   0.03173  -0.0545   0.2819   1.0000
   9.750   1.2501   0.04261   0.03384  -0.0529   0.2650   1.0000
  10.000   1.2650   0.04467   0.03602  -0.0515   0.2494   1.0000
  10.250   1.2799   0.04682   0.03830  -0.0500   0.2351   1.0000
  10.500   1.2968   0.04909   0.04065  -0.0489   0.2219   1.0000
  10.750   1.3161   0.05135   0.04292  -0.0482   0.2087   1.0000
  11.000   1.3008   0.05457   0.04671  -0.0438   0.2033   1.0000
  11.250   1.3179   0.05709   0.04925  -0.0429   0.1925   1.0000
  11.500   1.2962   0.06060   0.05321  -0.0384   0.1889   1.0000
  11.750   1.3183   0.06326   0.05585  -0.0382   0.1786   1.0000
  12.000   1.2886   0.06705   0.06001  -0.0335   0.1775   1.0000
  12.250   1.2561   0.07146   0.06470  -0.0299   0.1770   1.0000
  12.500   1.2206   0.07675   0.07023  -0.0276   0.1773   1.0000
  12.750   1.1825   0.08322   0.07689  -0.0269   0.1781   1.0000
  13.000   1.1440   0.09098   0.08476  -0.0281   0.1792   1.0000
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