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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 50,000
Max Cl/Cd: 29.72 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh64-il-50000.txt
Download as CSV file: xf-mh64-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 64  8.59%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5243   0.10282   0.09665   0.0169   1.0000   0.2455
  -8.000  -0.5357   0.10063   0.09459   0.0144   1.0000   0.2546
  -7.750  -0.5304   0.09714   0.09115   0.0141   1.0000   0.2668
  -7.500  -0.5198   0.09311   0.08716   0.0144   1.0000   0.2795
  -7.250  -0.5146   0.08951   0.08363   0.0142   1.0000   0.2928
  -7.000  -0.5054   0.08555   0.07973   0.0143   1.0000   0.3038
  -6.750  -0.5433   0.06981   0.06385  -0.0170   1.0000   0.1434
  -6.500  -0.5357   0.06096   0.05476  -0.0229   1.0000   0.1121
  -6.250  -0.5269   0.05397   0.04735  -0.0266   1.0000   0.0990
  -6.000  -0.5148   0.04759   0.04024  -0.0288   1.0000   0.0897
  -5.750  -0.4972   0.04308   0.03537  -0.0291   1.0000   0.0866
  -5.500  -0.4781   0.03901   0.03077  -0.0290   1.0000   0.0861
  -5.250  -0.4569   0.03557   0.02675  -0.0286   1.0000   0.0887
  -5.000  -0.4336   0.03255   0.02299  -0.0277   1.0000   0.0918
  -4.750  -0.4098   0.02944   0.01980  -0.0269   1.0000   0.0964
  -4.500  -0.3841   0.02702   0.01692  -0.0257   1.0000   0.1046
  -4.250  -0.3617   0.02490   0.01495  -0.0246   1.0000   0.1286
  -4.000  -0.3398   0.02278   0.01296  -0.0230   1.0000   0.1733
  -3.750  -0.3237   0.02017   0.01139  -0.0204   1.0000   0.3157
  -3.500  -0.3159   0.01909   0.01105  -0.0160   1.0000   0.4609
  -3.250  -0.3059   0.01844   0.01080  -0.0116   1.0000   0.5587
  -3.000  -0.2949   0.01774   0.01042  -0.0071   1.0000   0.6472
  -2.750  -0.2839   0.01704   0.01005  -0.0020   1.0000   0.7405
  -2.500  -0.1489   0.01666   0.00914  -0.0154   1.0000   0.9606
  -2.250  -0.0923   0.01580   0.00772  -0.0249   1.0000   1.0000
  -2.000  -0.1016   0.01568   0.00740  -0.0209   1.0000   1.0000
  -1.750  -0.0990   0.01574   0.00719  -0.0181   1.0000   1.0000
  -1.500  -0.0905   0.01587   0.00705  -0.0159   1.0000   1.0000
  -1.250  -0.0788   0.01605   0.00698  -0.0142   1.0000   1.0000
  -1.000  -0.0651   0.01626   0.00697  -0.0128   1.0000   1.0000
  -0.750  -0.0504   0.01652   0.00699  -0.0117   1.0000   1.0000
  -0.500  -0.0348   0.01682   0.00711  -0.0107   1.0000   1.0000
  -0.250  -0.0189   0.01716   0.00729  -0.0099   1.0000   1.0000
   0.000  -0.0027   0.01755   0.00754  -0.0092   1.0000   1.0000
   0.250   0.0137   0.01799   0.00785  -0.0086   1.0000   1.0000
   0.500   0.0301   0.01848   0.00821  -0.0082   1.0000   1.0000
   0.750   0.0581   0.01918   0.00882  -0.0101   0.9950   1.0000
   1.000   0.1196   0.02026   0.00985  -0.0181   0.9744   1.0000
   1.250   0.1823   0.02127   0.01086  -0.0259   0.9532   1.0000
   1.500   0.2409   0.02210   0.01173  -0.0325   0.9306   1.0000
   1.750   0.2972   0.02279   0.01251  -0.0384   0.9072   1.0000
   2.000   0.3558   0.02332   0.01319  -0.0440   0.8837   1.0000
   2.250   0.4092   0.02368   0.01368  -0.0479   0.8603   1.0000
   2.500   0.4447   0.02409   0.01419  -0.0485   0.8350   1.0000
   2.750   0.4758   0.02445   0.01471  -0.0481   0.8096   1.0000
   3.000   0.5037   0.02475   0.01511  -0.0468   0.7842   1.0000
   3.250   0.5296   0.02497   0.01543  -0.0449   0.7591   1.0000
   3.500   0.5542   0.02509   0.01564  -0.0425   0.7343   1.0000
   3.750   0.5784   0.02506   0.01573  -0.0397   0.7100   1.0000
   4.000   0.6005   0.02509   0.01585  -0.0368   0.6837   1.0000
   4.250   0.6225   0.02507   0.01591  -0.0338   0.6567   1.0000
   4.500   0.6447   0.02497   0.01587  -0.0308   0.6291   1.0000
   4.750   0.6665   0.02501   0.01598  -0.0280   0.5989   1.0000
   5.000   0.6886   0.02505   0.01608  -0.0253   0.5674   1.0000
   5.250   0.7115   0.02502   0.01612  -0.0225   0.5358   1.0000
   5.500   0.7338   0.02528   0.01639  -0.0201   0.5010   1.0000
   5.750   0.7567   0.02555   0.01658  -0.0176   0.4663   1.0000
   6.000   0.7786   0.02620   0.01722  -0.0156   0.4284   1.0000
   6.250   0.8006   0.02700   0.01798  -0.0138   0.3910   1.0000
   6.500   0.8228   0.02788   0.01874  -0.0119   0.3548   1.0000
   6.750   0.8440   0.02903   0.01987  -0.0104   0.3180   1.0000
   7.000   0.8645   0.03035   0.02132  -0.0089   0.2818   1.0000
   7.250   0.8854   0.03166   0.02243  -0.0073   0.2470   1.0000
   7.500   0.9041   0.03363   0.02457  -0.0059   0.2140   1.0000
   7.750   0.9229   0.03529   0.02603  -0.0044   0.1813   1.0000
   8.000   0.9404   0.03803   0.02897  -0.0030   0.1564   1.0000
   8.250   0.9552   0.04081   0.03197  -0.0017   0.1348   1.0000
   8.500   0.9696   0.04470   0.03621  -0.0005   0.1225   1.0000
   8.750   0.9802   0.04794   0.03972   0.0007   0.1093   1.0000
   9.000   0.9940   0.05167   0.04349   0.0017   0.1002   1.0000
   9.250   0.9911   0.05686   0.04937   0.0026   0.0986   1.0000
   9.500   0.9839   0.06214   0.05511   0.0032   0.0981   1.0000
   9.750   0.9717   0.06743   0.06074   0.0032   0.0983   1.0000
  10.000   0.9563   0.07268   0.06619   0.0028   0.0990   1.0000
  10.250   0.9381   0.07777   0.07140   0.0022   0.0998   1.0000
  10.500   0.9227   0.08323   0.07690   0.0007   0.1005   1.0000
  10.750   0.8415   0.10109   0.09472  -0.0166   0.1256   1.0000
  11.000   0.7997   0.11629   0.10967  -0.0290   0.1502   1.0000
  11.250   0.8185   0.11909   0.11256  -0.0262   0.1401   1.0000
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