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MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 25 9.98% (mh25-il)
Reynolds number: 200,000
Max Cl/Cd: 70.87 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh25-il-200000.txt
Download as CSV file: xf-mh25-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 25  9.98%                                    
  
 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  -0.5070   0.08880   0.08551  -0.0326   1.0000   0.0351
  -8.500  -0.5211   0.08512   0.08190  -0.0332   1.0000   0.0354
  -8.250  -0.5403   0.08163   0.07844  -0.0337   1.0000   0.0351
  -8.000  -0.5637   0.07899   0.07580  -0.0314   1.0000   0.0350
  -7.750  -0.5830   0.07629   0.07309  -0.0287   1.0000   0.0350
  -7.500  -0.5965   0.07309   0.06986  -0.0265   1.0000   0.0355
  -7.250  -0.6065   0.07000   0.06671  -0.0243   1.0000   0.0360
  -7.000  -0.6149   0.06671   0.06334  -0.0219   1.0000   0.0369
  -6.750  -0.6203   0.06350   0.06002  -0.0196   1.0000   0.0378
  -6.500  -0.6236   0.06014   0.05648  -0.0170   1.0000   0.0397
  -6.250  -0.6234   0.05954   0.05531  -0.0129   1.0000   0.0424
  -6.000  -0.6313   0.05396   0.04948  -0.0099   1.0000   0.0432
  -5.750  -0.6266   0.04945   0.04506  -0.0083   1.0000   0.0447
  -5.500  -0.6188   0.04696   0.04255  -0.0063   1.0000   0.0463
  -5.250  -0.6104   0.04458   0.04002  -0.0040   1.0000   0.0486
  -5.000  -0.5982   0.04596   0.04065   0.0003   1.0000   0.0555
  -4.750  -0.5926   0.03921   0.03398   0.0014   1.0000   0.0580
  -4.500  -0.5787   0.03705   0.03175   0.0031   1.0000   0.0610
  -4.250  -0.5665   0.03511   0.02939   0.0056   1.0000   0.0707
  -4.000  -0.5364   0.02830   0.02164   0.0103   1.0000   0.0273
  -3.750  -0.5125   0.02613   0.01880   0.0131   0.9999   0.0206
  -3.500  -0.4796   0.02319   0.01555   0.0124   0.9970   0.0189
  -3.250  -0.4442   0.02134   0.01335   0.0115   0.9942   0.0183
  -3.000  -0.4114   0.01996   0.01182   0.0109   0.9902   0.0183
  -2.750  -0.3786   0.01896   0.01071   0.0101   0.9860   0.0188
  -2.500  -0.3429   0.01829   0.00994   0.0085   0.9825   0.0207
  -2.250  -0.3163   0.01718   0.00884   0.0089   0.9766   0.0436
  -2.000  -0.2966   0.01405   0.00972   0.0119   0.9766   0.9114
  -1.750  -0.1563   0.01601   0.01117  -0.0089   0.9910   0.9846
  -1.500  -0.0741   0.01641   0.01130  -0.0204   0.9950   1.0000
  -1.250  -0.0335   0.01643   0.01118  -0.0237   0.9893   1.0000
  -1.000   0.0097   0.01654   0.01114  -0.0276   0.9840   1.0000
  -0.750   0.0480   0.01657   0.01108  -0.0304   0.9777   1.0000
  -0.500   0.0905   0.01662   0.01105  -0.0339   0.9719   1.0000
  -0.250   0.1286   0.01661   0.01097  -0.0365   0.9652   1.0000
   0.000   0.1711   0.01658   0.01089  -0.0400   0.9591   1.0000
   0.250   0.2101   0.01652   0.01080  -0.0426   0.9522   1.0000
   0.500   0.2528   0.01641   0.01068  -0.0460   0.9459   1.0000
   0.750   0.2925   0.01625   0.01053  -0.0486   0.9388   1.0000
   1.000   0.3369   0.01602   0.01031  -0.0521   0.9325   1.0000
   1.250   0.3763   0.01577   0.01010  -0.0546   0.9251   1.0000
   1.500   0.4231   0.01542   0.00979  -0.0584   0.9192   1.0000
   1.750   0.4798   0.01492   0.00937  -0.0642   0.9157   1.0000
   2.000   0.5163   0.01447   0.00899  -0.0657   0.9057   1.0000
   2.250   0.5530   0.01394   0.00859  -0.0671   0.8958   1.0000
   2.500   0.5928   0.01329   0.00802  -0.0690   0.8864   1.0000
   2.750   0.6205   0.01273   0.00756  -0.0685   0.8722   1.0000
   3.000   0.6437   0.01221   0.00715  -0.0669   0.8539   1.0000
   3.250   0.6672   0.01174   0.00676  -0.0654   0.8305   1.0000
   3.500   0.7008   0.01116   0.00621  -0.0657   0.7988   1.0000
   3.750   0.7403   0.01068   0.00561  -0.0672   0.7436   1.0000
   4.000   0.7654   0.01080   0.00543  -0.0661   0.6704   1.0000
   4.250   0.7810   0.01124   0.00559  -0.0633   0.5987   1.0000
   4.500   0.7929   0.01178   0.00582  -0.0601   0.5290   1.0000
   4.750   0.8035   0.01237   0.00612  -0.0567   0.4636   1.0000
   5.000   0.8133   0.01300   0.00647  -0.0533   0.4002   1.0000
   5.250   0.8235   0.01363   0.00685  -0.0500   0.3401   1.0000
   5.500   0.8333   0.01431   0.00726  -0.0468   0.2818   1.0000
   5.750   0.8434   0.01500   0.00771  -0.0437   0.2275   1.0000
   6.000   0.8535   0.01574   0.00820  -0.0406   0.1766   1.0000
   6.250   0.8633   0.01652   0.00877  -0.0374   0.1344   1.0000
   6.500   0.8717   0.01742   0.00947  -0.0340   0.0971   1.0000
   6.750   0.8794   0.01837   0.01028  -0.0304   0.0715   1.0000
   7.000   0.8865   0.01932   0.01120  -0.0265   0.0576   1.0000
   7.250   0.8922   0.02042   0.01239  -0.0224   0.0504   1.0000
   7.500   0.9011   0.02133   0.01335  -0.0189   0.0447   1.0000
   7.750   0.9098   0.02284   0.01489  -0.0155   0.0402   1.0000
   8.000   0.9219   0.02361   0.01580  -0.0126   0.0355   1.0000
   8.250   0.9369   0.02606   0.01825  -0.0108   0.0300   1.0000
   8.500   0.9474   0.02662   0.01904  -0.0074   0.0269   1.0000
   8.750   0.9538   0.02737   0.01986  -0.0037   0.0225   1.0000
   9.000   0.9654   0.03030   0.02305  -0.0014   0.0190   1.0000
   9.250   0.9738   0.03193   0.02498   0.0022   0.0167   1.0000
   9.500   0.9813   0.03435   0.02772   0.0055   0.0161   1.0000
   9.750   0.9835   0.03695   0.03065   0.0095   0.0158   1.0000
  10.000   0.9796   0.03954   0.03356   0.0143   0.0156   1.0000
  10.250   0.9699   0.04208   0.03640   0.0197   0.0153   1.0000
  10.500   0.9578   0.04490   0.03954   0.0248   0.0157   1.0000
  10.750   0.9419   0.04799   0.04294   0.0297   0.0158   1.0000
  11.000   0.9247   0.05125   0.04646   0.0337   0.0161   1.0000
  11.250   0.9061   0.05465   0.05010   0.0370   0.0163   1.0000
  11.500   0.8859   0.05843   0.05411   0.0392   0.0166   1.0000
  11.750   0.8658   0.06246   0.05833   0.0402   0.0168   1.0000
  12.000   0.8431   0.06731   0.06336   0.0398   0.0169   1.0000
  12.250   0.8197   0.07311   0.06932   0.0375   0.0170   1.0000
  12.500   0.8001   0.07932   0.07567   0.0339   0.0172   1.0000
  12.750   0.7780   0.08741   0.08387   0.0284   0.0175   1.0000
  13.000   0.7578   0.09670   0.09324   0.0220   0.0178   1.0000
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