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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 100,000
Max Cl/Cd: 61.39 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh38-il-100000.txt
Download as CSV file: xf-mh38-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 38  9.68%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3242   0.10406   0.09941  -0.0380   1.0000   0.0826
  -8.750  -0.3363   0.10269   0.09817  -0.0418   1.0000   0.0838
  -8.500  -0.3504   0.10125   0.09689  -0.0445   1.0000   0.0842
  -8.250  -0.3189   0.09435   0.08992  -0.0396   1.0000   0.0876
  -8.000  -0.3163   0.09175   0.08740  -0.0390   1.0000   0.0902
  -7.750  -0.3222   0.08969   0.08546  -0.0383   1.0000   0.0928
  -7.500  -0.3395   0.08880   0.08473  -0.0358   1.0000   0.0942
  -7.250  -0.3688   0.08917   0.08527  -0.0302   1.0000   0.0943
  -7.000  -0.3948   0.08932   0.08553  -0.0254   1.0000   0.0940
  -6.750  -0.4171   0.08860   0.08492  -0.0234   1.0000   0.0950
  -6.500  -0.4072   0.08231   0.07860  -0.0414   0.9913   0.0983
  -6.250  -0.3872   0.07888   0.07520  -0.0369   0.9875   0.1012
  -6.000  -0.3556   0.07113   0.06720  -0.0581   0.9761   0.1117
  -5.750  -0.3347   0.06727   0.06343  -0.0558   0.9715   0.1141
  -5.500  -0.3006   0.04880   0.04417  -0.0754   0.9630   0.0601
  -5.250  -0.2683   0.04171   0.03657  -0.0809   0.9571   0.0538
  -5.000  -0.2349   0.03588   0.02993  -0.0854   0.9513   0.0553
  -4.750  -0.2006   0.03134   0.02432  -0.0879   0.9451   0.0578
  -4.500  -0.1615   0.02812   0.02080  -0.0910   0.9414   0.0668
  -4.250  -0.1328   0.02619   0.01847  -0.0916   0.9343   0.0785
  -4.000  -0.0935   0.02461   0.01636  -0.0937   0.9295   0.0985
  -3.750  -0.0598   0.02345   0.01517  -0.0951   0.9239   0.1190
  -3.500  -0.0265   0.02242   0.01402  -0.0962   0.9178   0.1421
  -3.250   0.0164   0.02158   0.01315  -0.0992   0.9142   0.1771
  -3.000   0.0408   0.02109   0.01269  -0.0988   0.9062   0.2049
  -2.750   0.0804   0.02041   0.01209  -0.1011   0.9018   0.2492
  -2.500   0.1073   0.01999   0.01184  -0.1012   0.8949   0.2945
  -2.250   0.1400   0.01940   0.01156  -0.1022   0.8893   0.3661
  -2.000   0.1700   0.01880   0.01145  -0.1026   0.8838   0.4801
  -1.500   0.2442   0.01729   0.01114  -0.1036   0.8743   1.0000
  -1.250   0.2683   0.01763   0.01119  -0.1035   0.8660   1.0000
  -1.000   0.3037   0.01772   0.01101  -0.1049   0.8607   1.0000
  -0.750   0.3265   0.01810   0.01120  -0.1043   0.8524   1.0000
  -0.500   0.3604   0.01819   0.01108  -0.1053   0.8470   1.0000
  -0.250   0.3825   0.01861   0.01137  -0.1047   0.8385   1.0000
   0.000   0.4156   0.01869   0.01131  -0.1054   0.8332   1.0000
   0.250   0.4371   0.01915   0.01167  -0.1046   0.8245   1.0000
   0.500   0.4700   0.01921   0.01162  -0.1052   0.8193   1.0000
   0.750   0.4909   0.01971   0.01205  -0.1044   0.8103   1.0000
   1.000   0.5239   0.01973   0.01198  -0.1048   0.8053   1.0000
   1.250   0.5443   0.02026   0.01248  -0.1039   0.7959   1.0000
   1.500   0.5777   0.02022   0.01239  -0.1043   0.7912   1.0000
   1.750   0.5977   0.02078   0.01294  -0.1034   0.7813   1.0000
   2.000   0.6286   0.02083   0.01295  -0.1034   0.7758   1.0000
   2.250   0.6514   0.02125   0.01338  -0.1027   0.7666   1.0000
   2.500   0.6758   0.02161   0.01378  -0.1021   0.7582   1.0000
   2.750   0.7058   0.02162   0.01379  -0.1019   0.7517   1.0000
   3.000   0.7280   0.02208   0.01429  -0.1011   0.7419   1.0000
   3.250   0.7612   0.02184   0.01406  -0.1011   0.7366   1.0000
   3.500   0.7827   0.02230   0.01463  -0.1001   0.7258   1.0000
   3.750   0.8073   0.02257   0.01496  -0.0994   0.7164   1.0000
   4.000   0.8394   0.02229   0.01472  -0.0991   0.7099   1.0000
   4.250   0.8624   0.02260   0.01513  -0.0982   0.6988   1.0000
   4.500   0.8876   0.02275   0.01542  -0.0973   0.6886   1.0000
   4.750   0.9212   0.02226   0.01499  -0.0970   0.6818   1.0000
   5.000   0.9452   0.02241   0.01527  -0.0960   0.6699   1.0000
   5.250   0.9703   0.02246   0.01544  -0.0951   0.6581   1.0000
   5.500   0.9966   0.02238   0.01549  -0.0941   0.6461   1.0000
   5.750   1.0237   0.02219   0.01543  -0.0932   0.6337   1.0000
   6.000   1.0511   0.02190   0.01534  -0.0921   0.6201   1.0000
   6.250   1.0787   0.02151   0.01508  -0.0910   0.6050   1.0000
   6.500   1.1076   0.02086   0.01453  -0.0898   0.5880   1.0000
   6.750   1.1313   0.02037   0.01418  -0.0880   0.5645   1.0000
   7.000   1.1548   0.01969   0.01356  -0.0859   0.5349   1.0000
   7.250   1.1741   0.01938   0.01333  -0.0835   0.4977   1.0000
   7.500   1.1904   0.01939   0.01328  -0.0808   0.4498   1.0000
   7.750   1.1991   0.02001   0.01365  -0.0773   0.3771   1.0000
   8.000   1.1935   0.02184   0.01480  -0.0725   0.2606   1.0000
   8.250   1.1725   0.02524   0.01702  -0.0666   0.1300   1.0000
   8.500   1.1564   0.02825   0.01945  -0.0611   0.0830   1.0000
   8.750   1.1483   0.03082   0.02183  -0.0571   0.0647   1.0000
   9.000   1.1463   0.03320   0.02420  -0.0538   0.0540   1.0000
   9.250   1.1497   0.03547   0.02649  -0.0514   0.0456   1.0000
   9.500   1.1623   0.03832   0.02918  -0.0494   0.0396   1.0000
   9.750   1.1937   0.04070   0.03175  -0.0486   0.0360   1.0000
  10.000   1.2166   0.04313   0.03431  -0.0479   0.0323   1.0000
  10.250   1.2607   0.04904   0.04036  -0.0502   0.0289   1.0000
  10.500   1.2752   0.05267   0.04437  -0.0489   0.0287   1.0000
  10.750   1.2832   0.05673   0.04881  -0.0471   0.0288   1.0000
  11.000   1.2896   0.06203   0.05450  -0.0458   0.0291   1.0000
  11.250   1.2864   0.06443   0.05718  -0.0429   0.0294   1.0000
  11.500   1.2793   0.06670   0.05973  -0.0401   0.0298   1.0000
  11.750   1.2682   0.06923   0.06259  -0.0376   0.0303   1.0000
  12.000   1.2511   0.07279   0.06654  -0.0357   0.0312   1.0000
  12.250   1.2256   0.07730   0.07143  -0.0349   0.0319   1.0000
  12.500   1.2001   0.08268   0.07716  -0.0352   0.0326   1.0000
  12.750   1.1759   0.08851   0.08327  -0.0365   0.0332   1.0000
  13.000   1.1515   0.09489   0.08989  -0.0388   0.0337   1.0000
  13.250   1.1267   0.10191   0.09712  -0.0422   0.0341   1.0000
  13.500   1.1025   0.10957   0.10495  -0.0466   0.0346   1.0000
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