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MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
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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