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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 200,000
Max Cl/Cd: 72.32 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh32-il-200000.txt
Download as CSV file: xf-mh32-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4131   0.09781   0.09428  -0.0256   1.0000   0.0343
  -8.750  -0.4150   0.09415   0.09068  -0.0296   1.0000   0.0357
  -8.500  -0.4154   0.09068   0.08726  -0.0326   1.0000   0.0361
  -8.250  -0.3513   0.07511   0.07200  -0.0352   1.0000   0.0379
  -8.000  -0.3471   0.07188   0.06879  -0.0345   1.0000   0.0388
  -7.750  -0.3472   0.06850   0.06546  -0.0346   1.0000   0.0397
  -7.500  -0.3518   0.06510   0.06211  -0.0349   1.0000   0.0404
  -7.250  -0.4378   0.07053   0.06725  -0.0456   1.0000   0.0367
  -7.000  -0.4466   0.06576   0.06257  -0.0437   1.0000   0.0377
  -6.750  -0.4488   0.06356   0.06042  -0.0411   1.0000   0.0385
  -6.500  -0.4512   0.06118   0.05804  -0.0394   1.0000   0.0392
  -6.250  -0.4526   0.05854   0.05538  -0.0381   1.0000   0.0400
  -6.000  -0.4521   0.05568   0.05246  -0.0372   1.0000   0.0413
  -5.750  -0.4491   0.05244   0.04911  -0.0367   1.0000   0.0429
  -5.500  -0.4426   0.04879   0.04527  -0.0368   1.0000   0.0456
  -5.250  -0.4356   0.04383   0.03969  -0.0375   1.0000   0.0502
  -5.000  -0.4166   0.04049   0.03641  -0.0382   0.9985   0.0521
  -4.750  -0.3826   0.03701   0.03271  -0.0415   0.9945   0.0558
  -4.500  -0.3442   0.02713   0.02151  -0.0418   0.9914   0.0226
  -4.250  -0.3102   0.02293   0.01664  -0.0430   0.9876   0.0196
  -4.000  -0.2734   0.02000   0.01307  -0.0441   0.9845   0.0183
  -3.750  -0.2346   0.01816   0.01094  -0.0459   0.9817   0.0194
  -3.500  -0.2012   0.01728   0.00991  -0.0469   0.9758   0.0233
  -3.250  -0.1646   0.01567   0.00823  -0.0485   0.9717   0.0300
  -3.000  -0.1250   0.01439   0.00693  -0.0507   0.9682   0.0512
  -2.750  -0.0956   0.01275   0.00605  -0.0515   0.9614   0.1994
  -2.500  -0.0586   0.01177   0.00585  -0.0539   0.9569   0.4044
  -2.250  -0.0290   0.01108   0.00577  -0.0543   0.9501   0.5778
  -2.000   0.0032   0.01054   0.00574  -0.0546   0.9446   0.7331
  -1.750   0.0427   0.01019   0.00570  -0.0556   0.9419   0.8673
  -1.500   0.1109   0.01003   0.00548  -0.0631   0.9424   0.9620
  -1.250   0.1814   0.00987   0.00513  -0.0717   0.9428   1.0000
  -1.000   0.2136   0.00976   0.00489  -0.0727   0.9332   1.0000
  -0.750   0.2506   0.00962   0.00462  -0.0744   0.9261   1.0000
  -0.500   0.2805   0.00950   0.00441  -0.0746   0.9163   1.0000
  -0.250   0.3062   0.00942   0.00425  -0.0739   0.9049   1.0000
   0.000   0.3312   0.00933   0.00409  -0.0730   0.8932   1.0000
   0.250   0.3554   0.00924   0.00393  -0.0718   0.8810   1.0000
   0.500   0.3790   0.00917   0.00378  -0.0705   0.8684   1.0000
   0.750   0.4026   0.00911   0.00366  -0.0692   0.8553   1.0000
   1.000   0.4263   0.00906   0.00355  -0.0679   0.8415   1.0000
   1.250   0.4502   0.00902   0.00346  -0.0667   0.8268   1.0000
   1.500   0.4745   0.00899   0.00339  -0.0656   0.8113   1.0000
   1.750   0.4992   0.00898   0.00332  -0.0645   0.7950   1.0000
   2.000   0.5241   0.00898   0.00325  -0.0635   0.7779   1.0000
   2.250   0.5487   0.00902   0.00325  -0.0626   0.7577   1.0000
   2.500   0.5739   0.00907   0.00325  -0.0617   0.7379   1.0000
   2.750   0.5987   0.00916   0.00329  -0.0608   0.7150   1.0000
   3.000   0.6236   0.00928   0.00333  -0.0599   0.6915   1.0000
   3.250   0.6484   0.00943   0.00340  -0.0591   0.6670   1.0000
   3.500   0.6730   0.00962   0.00351  -0.0582   0.6414   1.0000
   3.750   0.6975   0.00985   0.00368  -0.0574   0.6150   1.0000
   4.000   0.7217   0.01010   0.00385  -0.0565   0.5875   1.0000
   4.250   0.7458   0.01037   0.00405  -0.0557   0.5591   1.0000
   4.500   0.7697   0.01066   0.00428  -0.0549   0.5294   1.0000
   4.750   0.7933   0.01097   0.00456  -0.0540   0.4984   1.0000
   5.000   0.8165   0.01133   0.00483  -0.0531   0.4665   1.0000
   5.250   0.8395   0.01171   0.00514  -0.0522   0.4332   1.0000
   5.500   0.8619   0.01215   0.00548  -0.0513   0.3988   1.0000
   5.750   0.8843   0.01261   0.00587  -0.0504   0.3635   1.0000
   6.000   0.9059   0.01314   0.00629  -0.0494   0.3286   1.0000
   6.250   0.9276   0.01368   0.00675  -0.0485   0.2919   1.0000
   6.500   0.9485   0.01431   0.00731  -0.0475   0.2548   1.0000
   6.750   0.9688   0.01499   0.00787  -0.0464   0.2168   1.0000
   7.000   0.9889   0.01573   0.00848  -0.0454   0.1808   1.0000
   7.250   1.0088   0.01652   0.00919  -0.0443   0.1483   1.0000
   7.500   1.0271   0.01750   0.01003  -0.0431   0.1160   1.0000
   7.750   1.0437   0.01869   0.01108  -0.0416   0.0829   1.0000
   8.000   1.0582   0.02012   0.01240  -0.0397   0.0592   1.0000
   8.250   1.0738   0.02138   0.01363  -0.0381   0.0426   1.0000
   8.500   1.0858   0.02301   0.01528  -0.0359   0.0306   1.0000
   8.750   1.0980   0.02459   0.01698  -0.0338   0.0213   1.0000
   9.000   1.1042   0.02723   0.01974  -0.0308   0.0181   1.0000
   9.250   1.1180   0.02919   0.02189  -0.0288   0.0163   1.0000
   9.500   1.1318   0.03137   0.02426  -0.0269   0.0150   1.0000
   9.750   1.1447   0.03376   0.02686  -0.0251   0.0142   1.0000
  10.000   1.1555   0.03641   0.02976  -0.0231   0.0137   1.0000
  10.250   1.1614   0.03883   0.03238  -0.0209   0.0129   1.0000
  10.500   1.1618   0.04205   0.03583  -0.0184   0.0123   1.0000
  10.750   1.1558   0.04573   0.03984  -0.0155   0.0121   1.0000
  11.250   1.1303   0.05193   0.04664  -0.0104   0.0111   1.0000
  11.500   1.1242   0.05424   0.04919  -0.0092   0.0105   1.0000
  11.750   1.1112   0.05812   0.05332  -0.0087   0.0104   1.0000
  12.000   1.0970   0.06243   0.05787  -0.0091   0.0102   1.0000
  12.250   1.0811   0.06748   0.06314  -0.0105   0.0103   1.0000
  12.500   1.0638   0.07322   0.06909  -0.0131   0.0103   1.0000
  13.750   0.8204   0.12176   0.11889  -0.0396   0.0166   1.0000
  14.000   0.7903   0.13144   0.12864  -0.0457   0.0174   1.0000
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