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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 500,000
Max Cl/Cd: 122.68 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh38-il-500000.txt
Download as CSV file: xf-mh38-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3327   0.09413   0.09199  -0.0397   1.0000   0.0143
  -9.000  -0.3336   0.09034   0.08824  -0.0408   1.0000   0.0147
  -8.750  -0.3315   0.08725   0.08518  -0.0416   1.0000   0.0149
  -8.500  -0.3299   0.08441   0.08238  -0.0422   1.0000   0.0152
  -8.250  -0.3306   0.08154   0.07957  -0.0426   1.0000   0.0154
  -7.000  -0.2965   0.03102   0.02796  -0.0947   0.8765   0.0081
  -6.750  -0.2821   0.02727   0.02385  -0.0954   0.8650   0.0075
  -6.500  -0.2686   0.02199   0.01781  -0.0960   0.8548   0.0070
  -6.250  -0.2481   0.01873   0.01397  -0.0958   0.8461   0.0069
  -6.000  -0.2246   0.01644   0.01125  -0.0955   0.8376   0.0069
  -5.750  -0.1997   0.01483   0.00929  -0.0951   0.8304   0.0070
  -5.500  -0.1737   0.01367   0.00789  -0.0948   0.8226   0.0074
  -5.250  -0.1481   0.01230   0.00623  -0.0945   0.8159   0.0085
  -5.000  -0.1214   0.01144   0.00523  -0.0943   0.8087   0.0111
  -4.750  -0.0943   0.01073   0.00441  -0.0941   0.8024   0.0187
  -4.500  -0.0669   0.01039   0.00407  -0.0941   0.7956   0.0313
  -4.250  -0.0394   0.01014   0.00375  -0.0940   0.7899   0.0442
  -4.000  -0.0117   0.00985   0.00345  -0.0940   0.7833   0.0575
  -3.750   0.0159   0.00957   0.00315  -0.0940   0.7777   0.0738
  -3.500   0.0437   0.00933   0.00294  -0.0940   0.7715   0.0915
  -3.250   0.0715   0.00917   0.00276  -0.0940   0.7658   0.1099
  -3.000   0.0994   0.00898   0.00258  -0.0941   0.7602   0.1290
  -2.750   0.1273   0.00881   0.00241  -0.0941   0.7543   0.1503
  -2.500   0.1551   0.00866   0.00228  -0.0941   0.7492   0.1772
  -2.250   0.1831   0.00845   0.00218  -0.0942   0.7432   0.2118
  -2.000   0.2108   0.00827   0.00208  -0.0943   0.7380   0.2559
  -1.750   0.2386   0.00809   0.00202  -0.0944   0.7325   0.3059
  -1.500   0.2663   0.00787   0.00196  -0.0945   0.7269   0.3688
  -1.250   0.2938   0.00769   0.00192  -0.0945   0.7220   0.4377
  -0.750   0.3483   0.00725   0.00191  -0.0944   0.7109   0.5990
  -0.500   0.3743   0.00699   0.00194  -0.0940   0.7056   0.6969
  -0.250   0.3976   0.00668   0.00198  -0.0928   0.7000   0.8131
   0.000   0.4262   0.00642   0.00193  -0.0923   0.6952   0.9644
   0.250   0.4603   0.00642   0.00190  -0.0937   0.6892   1.0000
   0.500   0.4882   0.00648   0.00189  -0.0937   0.6837   1.0000
   0.750   0.5161   0.00655   0.00190  -0.0937   0.6781   1.0000
   1.000   0.5439   0.00661   0.00191  -0.0937   0.6722   1.0000
   1.250   0.5718   0.00669   0.00194  -0.0937   0.6668   1.0000
   1.500   0.5997   0.00674   0.00197  -0.0937   0.6603   1.0000
   1.750   0.6274   0.00684   0.00200  -0.0937   0.6546   1.0000
   2.000   0.6552   0.00688   0.00206  -0.0937   0.6477   1.0000
   2.250   0.6829   0.00698   0.00211  -0.0936   0.6414   1.0000
   2.500   0.7107   0.00703   0.00218  -0.0936   0.6341   1.0000
   3.000   0.7659   0.00719   0.00232  -0.0935   0.6193   1.0000
   3.250   0.7933   0.00728   0.00241  -0.0935   0.6120   1.0000
   3.500   0.8208   0.00736   0.00250  -0.0934   0.6034   1.0000
   3.750   0.8482   0.00745   0.00261  -0.0933   0.5949   1.0000
   4.000   0.8753   0.00757   0.00270  -0.0932   0.5860   1.0000
   4.250   0.9025   0.00766   0.00285  -0.0931   0.5755   1.0000
   4.500   0.9295   0.00776   0.00298  -0.0930   0.5643   1.0000
   4.750   0.9562   0.00789   0.00312  -0.0928   0.5518   1.0000
   5.000   0.9826   0.00803   0.00326  -0.0925   0.5368   1.0000
   5.250   1.0084   0.00822   0.00342  -0.0922   0.5184   1.0000
   5.500   1.0332   0.00845   0.00360  -0.0917   0.4898   1.0000
   5.750   1.0578   0.00875   0.00386  -0.0912   0.4609   1.0000
   6.000   1.0814   0.00914   0.00415  -0.0906   0.4267   1.0000
   6.250   1.1028   0.00972   0.00453  -0.0896   0.3786   1.0000
   6.500   1.1214   0.01056   0.00506  -0.0884   0.3146   1.0000
   6.750   1.1373   0.01166   0.00574  -0.0869   0.2368   1.0000
   7.000   1.1502   0.01303   0.00660  -0.0850   0.1527   1.0000
   7.250   1.1610   0.01453   0.00760  -0.0828   0.0752   1.0000
   7.500   1.1731   0.01586   0.00862  -0.0807   0.0288   1.0000
   7.750   1.1836   0.01731   0.01002  -0.0780   0.0102   1.0000
   8.000   1.1986   0.01826   0.01110  -0.0761   0.0081   1.0000
   8.250   1.2072   0.01961   0.01259  -0.0732   0.0070   1.0000
   8.500   1.2097   0.02103   0.01415  -0.0694   0.0067   1.0000
   8.750   1.2072   0.02275   0.01603  -0.0651   0.0064   1.0000
   9.000   1.2103   0.02431   0.01769  -0.0620   0.0063   1.0000
   9.250   1.2211   0.02536   0.01883  -0.0601   0.0061   1.0000
   9.500   1.2350   0.02618   0.01972  -0.0586   0.0056   1.0000
   9.750   1.2445   0.02743   0.02105  -0.0569   0.0052   1.0000
  10.000   1.2524   0.02893   0.02265  -0.0550   0.0050   1.0000
  10.250   1.2594   0.03067   0.02450  -0.0532   0.0048   1.0000
  10.500   1.2673   0.03239   0.02633  -0.0516   0.0047   1.0000
  10.750   1.2747   0.03440   0.02847  -0.0499   0.0046   1.0000
  11.000   1.2825   0.03637   0.03058  -0.0485   0.0044   1.0000
  11.250   1.2894   0.03844   0.03279  -0.0471   0.0043   1.0000
  11.500   1.2947   0.04042   0.03489  -0.0460   0.0040   1.0000
  11.750   1.2987   0.04287   0.03749  -0.0449   0.0039   1.0000
  12.000   1.3001   0.04583   0.04062  -0.0437   0.0037   1.0000
  12.250   1.3002   0.04899   0.04398  -0.0426   0.0037   1.0000
  12.500   1.2958   0.05282   0.04804  -0.0417   0.0037   1.0000
  12.750   1.2903   0.05668   0.05211  -0.0411   0.0037   1.0000
  13.000   1.2803   0.06122   0.05690  -0.0409   0.0036   1.0000
  13.250   1.2698   0.06590   0.06180  -0.0411   0.0037   1.0000
  13.500   1.2593   0.07067   0.06679  -0.0418   0.0037   1.0000
  13.750   1.1284   0.08153   0.07818  -0.0428   0.0038   1.0000
  14.000   1.1027   0.08996   0.08692  -0.0454   0.0041   1.0000
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