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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 50,000
Max Cl/Cd: 37.79 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh38-il-50000-n5.txt
Download as CSV file: xf-mh38-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3531   0.12864   0.12156  -0.0293   1.0000   0.0809
 -10.500  -0.3532   0.12614   0.11913  -0.0314   1.0000   0.0828
 -10.000  -0.3550   0.11577   0.10891  -0.0383   1.0000   0.0453
  -9.250  -0.3426   0.10481   0.09808  -0.0412   1.0000   0.0449
  -9.000  -0.3391   0.10124   0.09459  -0.0419   1.0000   0.0446
  -8.750  -0.3355   0.09788   0.09131  -0.0422   1.0000   0.0441
  -8.500  -0.3338   0.09464   0.08816  -0.0426   1.0000   0.0435
  -8.250  -0.3352   0.09144   0.08507  -0.0431   1.0000   0.0430
  -8.000  -0.3392   0.08856   0.08232  -0.0431   1.0000   0.0426
  -7.750  -0.3474   0.08605   0.07997  -0.0425   1.0000   0.0422
  -7.500  -0.3602   0.08401   0.07810  -0.0411   1.0000   0.0419
  -7.250  -0.3741   0.08196   0.07620  -0.0397   1.0000   0.0416
  -7.000  -0.3885   0.08003   0.07440  -0.0383   1.0000   0.0413
  -6.750  -0.4018   0.07772   0.07217  -0.0376   1.0000   0.0409
  -6.500  -0.3894   0.07192   0.06635  -0.0447   0.9917   0.0405
  -6.250  -0.3667   0.06445   0.05874  -0.0547   0.9814   0.0402
  -6.000  -0.3447   0.05683   0.05084  -0.0636   0.9709   0.0402
  -5.750  -0.3201   0.04959   0.04313  -0.0713   0.9615   0.0413
  -5.500  -0.2877   0.04217   0.03472  -0.0788   0.9545   0.0446
  -5.250  -0.2617   0.03933   0.03165  -0.0810   0.9462   0.0494
  -5.000  -0.2260   0.03509   0.02664  -0.0845   0.9409   0.0538
  -4.750  -0.1974   0.03268   0.02375  -0.0859   0.9331   0.0631
  -4.500  -0.1608   0.03018   0.02069  -0.0881   0.9281   0.0740
  -4.250  -0.1315   0.02887   0.01911  -0.0889   0.9207   0.0889
  -4.000  -0.0962   0.02741   0.01727  -0.0904   0.9155   0.1060
  -3.750  -0.0659   0.02649   0.01616  -0.0912   0.9086   0.1282
  -3.500  -0.0327   0.02559   0.01506  -0.0923   0.9027   0.1528
  -3.250  -0.0026   0.02496   0.01436  -0.0930   0.8961   0.1819
  -3.000   0.0285   0.02437   0.01373  -0.0939   0.8896   0.2151
  -2.750   0.0597   0.02384   0.01318  -0.0947   0.8836   0.2546
  -2.250   0.1189   0.02288   0.01243  -0.0958   0.8708   0.3717
  -2.000   0.1434   0.02250   0.01233  -0.0953   0.8633   0.4561
  -1.750   0.1701   0.02197   0.01220  -0.0946   0.8579   0.5749
  -1.500   0.1866   0.02159   0.01226  -0.0916   0.8500   0.7138
  -1.250   0.2356   0.02105   0.01177  -0.0946   0.8460   1.0000
  -1.000   0.2597   0.02137   0.01176  -0.0944   0.8376   1.0000
  -0.750   0.2929   0.02153   0.01161  -0.0955   0.8322   1.0000
  -0.500   0.3157   0.02189   0.01174  -0.0950   0.8236   1.0000
  -0.250   0.3484   0.02206   0.01164  -0.0959   0.8183   1.0000
   0.000   0.3703   0.02247   0.01189  -0.0953   0.8095   1.0000
   0.250   0.4029   0.02264   0.01187  -0.0960   0.8044   1.0000
   0.500   0.4240   0.02309   0.01220  -0.0953   0.7953   1.0000
   0.750   0.4542   0.02331   0.01228  -0.0957   0.7896   1.0000
   1.250   0.5042   0.02405   0.01285  -0.0951   0.7743   1.0000
   1.750   0.5541   0.02482   0.01353  -0.0944   0.7588   1.0000
   2.000   0.5818   0.02510   0.01377  -0.0944   0.7519   1.0000
   2.250   0.6042   0.02558   0.01425  -0.0937   0.7431   1.0000
   2.500   0.6343   0.02576   0.01442  -0.0938   0.7371   1.0000
   2.750   0.6549   0.02632   0.01505  -0.0930   0.7274   1.0000
   3.000   0.6830   0.02657   0.01533  -0.0928   0.7205   1.0000
   3.250   0.7066   0.02700   0.01581  -0.0922   0.7116   1.0000
   3.500   0.7289   0.02749   0.01637  -0.0915   0.7023   1.0000
   3.750   0.7598   0.02755   0.01656  -0.0915   0.6958   1.0000
   4.000   0.7798   0.02814   0.01724  -0.0905   0.6851   1.0000
   4.250   0.8026   0.02858   0.01780  -0.0897   0.6753   1.0000
   4.500   0.8343   0.02853   0.01786  -0.0896   0.6683   1.0000
   4.750   0.8545   0.02906   0.01854  -0.0885   0.6568   1.0000
   5.000   0.8763   0.02949   0.01920  -0.0875   0.6456   1.0000
   5.250   0.9000   0.02980   0.01967  -0.0866   0.6346   1.0000
   5.500   0.9267   0.02988   0.01994  -0.0859   0.6243   1.0000
   5.750   0.9556   0.02979   0.02004  -0.0852   0.6140   1.0000
   6.000   0.9782   0.03003   0.02050  -0.0840   0.6010   1.0000
   6.250   1.0017   0.03018   0.02097  -0.0828   0.5876   1.0000
   6.500   1.0261   0.03021   0.02124  -0.0816   0.5735   1.0000
   6.750   1.0473   0.03038   0.02166  -0.0801   0.5574   1.0000
   7.000   1.0668   0.03059   0.02213  -0.0783   0.5392   1.0000
   7.250   1.0919   0.03028   0.02207  -0.0767   0.5200   1.0000
   7.500   1.1097   0.03032   0.02235  -0.0744   0.4955   1.0000
   7.750   1.1289   0.02998   0.02215  -0.0718   0.4638   1.0000
   8.000   1.1391   0.03014   0.02234  -0.0684   0.4200   1.0000
   8.250   1.1441   0.03072   0.02274  -0.0647   0.3640   1.0000
   8.500   1.1424   0.03198   0.02381  -0.0608   0.3045   1.0000
   8.750   1.1359   0.03396   0.02541  -0.0572   0.2451   1.0000
   9.000   1.1268   0.03660   0.02765  -0.0543   0.1877   1.0000
   9.250   1.1152   0.03987   0.03046  -0.0520   0.1368   1.0000
   9.500   1.1056   0.04335   0.03359  -0.0502   0.1031   1.0000
   9.750   1.0991   0.04679   0.03684  -0.0486   0.0825   1.0000
  10.000   1.0950   0.05012   0.04007  -0.0474   0.0677   1.0000
  10.250   1.0935   0.05328   0.04323  -0.0464   0.0577   1.0000
  10.500   1.0921   0.05652   0.04645  -0.0453   0.0519   1.0000
  10.750   1.0974   0.05924   0.04937  -0.0441   0.0448   1.0000
  11.000   1.0991   0.06229   0.05235  -0.0434   0.0399   1.0000
  11.250   1.1140   0.06444   0.05488  -0.0416   0.0355   1.0000
  11.500   1.1316   0.06668   0.05736  -0.0399   0.0324   1.0000
  11.750   1.1431   0.06954   0.06029  -0.0389   0.0297   1.0000
  12.000   1.1506   0.07305   0.06414  -0.0381   0.0278   1.0000
  12.250   1.1516   0.07698   0.06846  -0.0380   0.0264   1.0000
  12.500   1.1482   0.08140   0.07323  -0.0382   0.0254   1.0000
  12.750   1.1419   0.08623   0.07838  -0.0389   0.0249   1.0000
  13.000   1.1322   0.09159   0.08404  -0.0403   0.0247   1.0000
  13.250   1.1194   0.09751   0.09023  -0.0423   0.0246   1.0000
  13.500   1.1051   0.10386   0.09684  -0.0451   0.0247   1.0000
  13.750   1.0893   0.11086   0.10406  -0.0486   0.0248   1.0000
  14.000   1.0725   0.11863   0.11203  -0.0531   0.0250   1.0000
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