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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 200,000
Max Cl/Cd: 59.5 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh64-il-200000.txt
Download as CSV file: xf-mh64-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5658   0.11267   0.10933   0.0173   1.0000   0.0365
  -9.500  -0.5650   0.10826   0.10496   0.0142   1.0000   0.0381
  -9.250  -0.5668   0.10374   0.10050   0.0093   1.0000   0.0394
  -9.000  -0.4946   0.09153   0.08860   0.0036   1.0000   0.0414
  -8.750  -0.4867   0.08797   0.08505   0.0039   1.0000   0.0426
  -8.500  -0.4834   0.08398   0.08108   0.0030   1.0000   0.0437
  -8.250  -0.4827   0.07957   0.07669   0.0013   1.0000   0.0448
  -8.000  -0.4847   0.07487   0.07203  -0.0008   1.0000   0.0459
  -7.750  -0.4894   0.06982   0.06701  -0.0036   1.0000   0.0470
  -7.500  -0.4983   0.06443   0.06168  -0.0074   1.0000   0.0479
  -7.250  -0.5105   0.05815   0.05540  -0.0134   1.0000   0.0482
  -7.000  -0.5170   0.05089   0.04804  -0.0195   1.0000   0.0496
  -6.750  -0.5252   0.04494   0.04138  -0.0255   1.0000   0.0528
  -6.500  -0.5195   0.03694   0.03352  -0.0267   1.0000   0.0549
  -6.250  -0.5034   0.03360   0.03020  -0.0271   1.0000   0.0572
  -6.000  -0.4884   0.02963   0.02600  -0.0281   1.0000   0.0616
  -5.750  -0.4750   0.02507   0.02110  -0.0293   1.0000   0.0689
  -5.500  -0.4741   0.02749   0.02184  -0.0260   1.0000   0.0243
  -5.250  -0.4496   0.02370   0.01723  -0.0244   1.0000   0.0194
  -5.000  -0.4246   0.02268   0.01601  -0.0237   1.0000   0.0186
  -4.750  -0.4062   0.02054   0.01364  -0.0222   1.0000   0.0181
  -4.500  -0.3929   0.01886   0.01177  -0.0198   1.0000   0.0179
  -4.250  -0.3658   0.01722   0.00997  -0.0198   0.9959   0.0182
  -4.000  -0.3279   0.01521   0.00781  -0.0218   0.9881   0.0190
  -3.750  -0.2879   0.01364   0.00615  -0.0244   0.9812   0.0240
  -3.500  -0.2549   0.01117   0.00461  -0.0261   0.9712   0.2064
  -3.250  -0.2206   0.01046   0.00444  -0.0279   0.9609   0.3465
  -3.000  -0.1880   0.01008   0.00428  -0.0288   0.9501   0.4248
  -2.750  -0.1602   0.00975   0.00418  -0.0286   0.9383   0.5033
  -2.500  -0.1361   0.00946   0.00407  -0.0274   0.9260   0.5739
  -2.250  -0.1146   0.00919   0.00401  -0.0256   0.9137   0.6471
  -2.000  -0.0944   0.00891   0.00397  -0.0232   0.9016   0.7263
  -1.750  -0.0729   0.00866   0.00395  -0.0209   0.8898   0.8148
  -1.500  -0.0353   0.00852   0.00390  -0.0217   0.8799   0.9049
  -1.250   0.0168   0.00849   0.00373  -0.0259   0.8711   0.9614
  -1.000   0.0680   0.00845   0.00354  -0.0304   0.8613   0.9951
  -0.750   0.0949   0.00846   0.00340  -0.0302   0.8485   1.0000
  -0.500   0.1163   0.00849   0.00330  -0.0288   0.8355   1.0000
  -0.250   0.1387   0.00853   0.00322  -0.0276   0.8227   1.0000
   0.000   0.1616   0.00857   0.00316  -0.0264   0.8098   1.0000
   0.250   0.1850   0.00862   0.00311  -0.0253   0.7968   1.0000
   0.500   0.2088   0.00866   0.00306  -0.0242   0.7836   1.0000
   0.750   0.2330   0.00871   0.00302  -0.0232   0.7702   1.0000
   1.000   0.2574   0.00876   0.00299  -0.0223   0.7563   1.0000
   1.250   0.2821   0.00880   0.00297  -0.0214   0.7419   1.0000
   1.500   0.3071   0.00885   0.00295  -0.0205   0.7269   1.0000
   1.750   0.3322   0.00891   0.00294  -0.0197   0.7114   1.0000
   2.000   0.3577   0.00896   0.00294  -0.0190   0.6943   1.0000
   2.250   0.3835   0.00902   0.00296  -0.0184   0.6756   1.0000
   2.500   0.4091   0.00910   0.00296  -0.0177   0.6569   1.0000
   2.750   0.4351   0.00918   0.00303  -0.0171   0.6352   1.0000
   3.000   0.4609   0.00929   0.00307  -0.0165   0.6131   1.0000
   3.250   0.4868   0.00942   0.00313  -0.0159   0.5887   1.0000
   3.500   0.5128   0.00958   0.00323  -0.0154   0.5625   1.0000
   3.750   0.5388   0.00977   0.00338  -0.0149   0.5351   1.0000
   4.000   0.5647   0.01000   0.00353  -0.0144   0.5068   1.0000
   4.250   0.5906   0.01027   0.00373  -0.0140   0.4776   1.0000
   4.500   0.6164   0.01056   0.00395  -0.0136   0.4475   1.0000
   4.750   0.6421   0.01089   0.00422  -0.0133   0.4172   1.0000
   5.000   0.6676   0.01126   0.00455  -0.0129   0.3866   1.0000
   5.250   0.6929   0.01166   0.00487  -0.0126   0.3560   1.0000
   5.500   0.7182   0.01207   0.00524  -0.0122   0.3240   1.0000
   5.750   0.7432   0.01254   0.00564  -0.0119   0.2918   1.0000
   6.000   0.7678   0.01306   0.00608  -0.0116   0.2596   1.0000
   6.250   0.7923   0.01361   0.00658  -0.0113   0.2272   1.0000
   6.500   0.8163   0.01424   0.00712  -0.0109   0.1966   1.0000
   6.750   0.8399   0.01493   0.00779  -0.0105   0.1678   1.0000
   7.000   0.8631   0.01567   0.00845  -0.0101   0.1396   1.0000
   7.250   0.8860   0.01646   0.00920  -0.0097   0.1115   1.0000
   7.500   0.9079   0.01741   0.01009  -0.0092   0.0829   1.0000
   7.750   0.9274   0.01882   0.01142  -0.0083   0.0582   1.0000
   8.000   0.9456   0.02034   0.01288  -0.0073   0.0410   1.0000
   8.250   0.9628   0.02196   0.01454  -0.0062   0.0295   1.0000
   8.500   0.9803   0.02356   0.01628  -0.0050   0.0223   1.0000
   8.750   0.9930   0.02595   0.01876  -0.0036   0.0177   1.0000
   9.000   1.0095   0.02793   0.02095  -0.0022   0.0156   1.0000
   9.250   1.0247   0.03019   0.02344  -0.0008   0.0144   1.0000
   9.500   1.0384   0.03270   0.02627   0.0006   0.0138   1.0000
   9.750   1.0493   0.03545   0.02932   0.0021   0.0134   1.0000
  10.000   1.0559   0.03861   0.03282   0.0037   0.0133   1.0000
  10.250   1.0567   0.04206   0.03664   0.0054   0.0133   1.0000
  10.500   1.0507   0.04554   0.04046   0.0075   0.0135   1.0000
  10.750   1.0374   0.04907   0.04429   0.0093   0.0137   1.0000
  11.000   1.0211   0.05311   0.04860   0.0098   0.0139   1.0000
  11.250   1.0038   0.05767   0.05341   0.0088   0.0141   1.0000
  11.500   0.9863   0.06279   0.05874   0.0066   0.0141   1.0000
  11.750   0.9655   0.06917   0.06533   0.0028   0.0144   1.0000
  12.000   0.9456   0.07629   0.07263  -0.0022   0.0145   1.0000
  12.250   0.9246   0.08464   0.08113  -0.0084   0.0147   1.0000
  12.500   0.9039   0.09395   0.09057  -0.0151   0.0150   1.0000
  12.750   0.8795   0.10535   0.10199  -0.0227   0.0154   1.0000
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