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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 500,000
Max Cl/Cd: 94.66 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh32-il-500000.txt
Download as CSV file: xf-mh32-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3381   0.09249   0.09035  -0.0256   1.0000   0.0138
  -9.250  -0.3370   0.08835   0.08624  -0.0271   1.0000   0.0141
  -9.000  -0.3357   0.08414   0.08204  -0.0287   1.0000   0.0145
  -8.750  -0.3333   0.08018   0.07810  -0.0305   1.0000   0.0150
  -8.500  -0.3322   0.07619   0.07413  -0.0319   1.0000   0.0152
  -8.250  -0.3328   0.07193   0.06989  -0.0335   1.0000   0.0153
  -8.000  -0.3346   0.06771   0.06570  -0.0350   1.0000   0.0153
  -7.750  -0.3388   0.06346   0.06149  -0.0364   1.0000   0.0153
  -7.500  -0.3474   0.05960   0.05768  -0.0373   1.0000   0.0153
  -7.250  -0.3701   0.05764   0.05579  -0.0345   1.0000   0.0153
  -7.000  -0.3728   0.05156   0.04969  -0.0418   0.9963   0.0153
  -6.750  -0.3601   0.04316   0.04113  -0.0510   0.9918   0.0154
  -6.500  -0.3453   0.03629   0.03404  -0.0572   0.9868   0.0154
  -6.250  -0.3253   0.03022   0.02767  -0.0622   0.9835   0.0155
  -6.000  -0.3201   0.01948   0.01645  -0.0673   0.9780   0.0168
  -5.750  -0.3292   0.03060   0.02713  -0.0669   0.9782   0.0171
  -5.500  -0.3001   0.02793   0.02428  -0.0689   0.9746   0.0181
  -5.250  -0.2686   0.02510   0.02116  -0.0709   0.9718   0.0194
  -5.000  -0.2337   0.01878   0.01382  -0.0704   0.9690   0.0092
  -4.750  -0.2095   0.01577   0.01048  -0.0697   0.9627   0.0080
  -4.500  -0.1799   0.01378   0.00818  -0.0698   0.9584   0.0075
  -4.250  -0.1512   0.01237   0.00658  -0.0696   0.9540   0.0075
  -4.000  -0.1267   0.01141   0.00549  -0.0687   0.9469   0.0078
  -3.750  -0.0994   0.01069   0.00465  -0.0682   0.9418   0.0087
  -3.500  -0.0760   0.00986   0.00369  -0.0671   0.9337   0.0117
  -3.250  -0.0507   0.00911   0.00303  -0.0662   0.9278   0.0463
  -3.000  -0.0273   0.00847   0.00276  -0.0655   0.9197   0.1328
  -2.750  -0.0025   0.00797   0.00253  -0.0650   0.9135   0.2212
  -2.250   0.0471   0.00715   0.00223  -0.0638   0.8986   0.3986
  -2.000   0.0715   0.00674   0.00212  -0.0631   0.8905   0.5014
  -1.750   0.0959   0.00640   0.00204  -0.0623   0.8826   0.5941
  -1.500   0.1202   0.00610   0.00196  -0.0613   0.8746   0.6783
  -1.250   0.1439   0.00584   0.00193  -0.0601   0.8652   0.7566
  -1.000   0.1673   0.00564   0.00189  -0.0587   0.8561   0.8251
  -0.750   0.1909   0.00549   0.00183  -0.0572   0.8465   0.8854
  -0.500   0.2209   0.00540   0.00177  -0.0571   0.8352   0.9375
  -0.250   0.2627   0.00537   0.00168  -0.0599   0.8241   0.9704
   0.000   0.3062   0.00535   0.00159  -0.0631   0.8123   0.9892
   0.250   0.3449   0.00535   0.00151  -0.0655   0.7989   1.0000
   0.500   0.3689   0.00539   0.00146  -0.0646   0.7836   1.0000
   0.750   0.3933   0.00544   0.00142  -0.0638   0.7673   1.0000
   1.000   0.4178   0.00551   0.00139  -0.0630   0.7493   1.0000
   1.250   0.4425   0.00559   0.00139  -0.0623   0.7294   1.0000
   1.500   0.4673   0.00570   0.00140  -0.0615   0.7087   1.0000
   1.750   0.4921   0.00582   0.00142  -0.0609   0.6859   1.0000
   2.000   0.5172   0.00597   0.00146  -0.0602   0.6626   1.0000
   2.250   0.5422   0.00613   0.00152  -0.0596   0.6389   1.0000
   2.500   0.5672   0.00631   0.00159  -0.0590   0.6148   1.0000
   2.750   0.5925   0.00649   0.00170  -0.0585   0.5905   1.0000
   3.000   0.6178   0.00668   0.00180  -0.0580   0.5665   1.0000
   3.250   0.6431   0.00689   0.00192  -0.0575   0.5416   1.0000
   3.500   0.6683   0.00710   0.00205  -0.0570   0.5162   1.0000
   3.750   0.6935   0.00734   0.00221  -0.0565   0.4894   1.0000
   4.000   0.7185   0.00759   0.00237  -0.0560   0.4611   1.0000
   4.250   0.7435   0.00786   0.00255  -0.0555   0.4327   1.0000
   4.500   0.7683   0.00815   0.00275  -0.0550   0.4031   1.0000
   4.750   0.7929   0.00847   0.00299  -0.0545   0.3730   1.0000
   5.250   0.8418   0.00916   0.00349  -0.0535   0.3128   1.0000
   5.500   0.8657   0.00958   0.00378  -0.0530   0.2784   1.0000
   5.750   0.8892   0.01004   0.00409  -0.0524   0.2432   1.0000
   6.000   0.9127   0.01050   0.00443  -0.0518   0.2105   1.0000
   6.250   0.9364   0.01095   0.00482  -0.0512   0.1833   1.0000
   6.500   0.9598   0.01144   0.00522  -0.0506   0.1568   1.0000
   6.750   0.9827   0.01197   0.00565  -0.0500   0.1304   1.0000
   7.000   1.0051   0.01254   0.00612  -0.0493   0.1045   1.0000
   7.250   1.0268   0.01320   0.00665  -0.0485   0.0781   1.0000
   7.500   1.0472   0.01399   0.00726  -0.0475   0.0505   1.0000
   7.750   1.0678   0.01474   0.00792  -0.0466   0.0324   1.0000
   8.000   1.0883   0.01550   0.00865  -0.0456   0.0219   1.0000
   8.250   1.1047   0.01677   0.00997  -0.0438   0.0094   1.0000
   8.500   1.1208   0.01800   0.01128  -0.0421   0.0062   1.0000
   8.750   1.1405   0.01874   0.01212  -0.0409   0.0052   1.0000
   9.000   1.1579   0.01969   0.01318  -0.0394   0.0046   1.0000
   9.250   1.1745   0.02066   0.01422  -0.0380   0.0039   1.0000
   9.500   1.1826   0.02241   0.01616  -0.0352   0.0035   1.0000
   9.750   1.1846   0.02472   0.01869  -0.0318   0.0032   1.0000
  10.000   1.1964   0.02583   0.01994  -0.0296   0.0031   1.0000
  10.250   1.2035   0.02718   0.02144  -0.0268   0.0029   1.0000
  10.500   1.2076   0.02882   0.02325  -0.0239   0.0028   1.0000
  10.750   1.2092   0.03078   0.02541  -0.0209   0.0027   1.0000
  11.000   1.2097   0.03288   0.02772  -0.0182   0.0026   1.0000
  11.250   1.2075   0.03535   0.03041  -0.0157   0.0026   1.0000
  11.500   1.2028   0.03812   0.03341  -0.0134   0.0025   1.0000
  11.750   1.1952   0.04132   0.03685  -0.0116   0.0026   1.0000
  12.000   1.1856   0.04487   0.04063  -0.0103   0.0025   1.0000
  12.250   1.1742   0.04882   0.04481  -0.0098   0.0026   1.0000
  12.500   1.1605   0.05338   0.04963  -0.0101   0.0026   1.0000
  12.750   1.1475   0.05824   0.05469  -0.0114   0.0027   1.0000
  13.000   1.1296   0.06432   0.06099  -0.0138   0.0027   1.0000
  13.250   1.1131   0.07077   0.06759  -0.0170   0.0027   1.0000
  13.500   1.0955   0.07799   0.07500  -0.0211   0.0027   1.0000
  13.750   1.0811   0.08516   0.08231  -0.0255   0.0027   1.0000
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