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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 100,000
Max Cl/Cd: 48.5 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh30-il-100000-n5.txt
Download as CSV file: xf-mh30-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 30  7.84%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4912   0.11182   0.10670  -0.0100   1.0000   0.0224
  -9.750  -0.4879   0.10791   0.10282  -0.0114   1.0000   0.0210
  -9.500  -0.4861   0.10370   0.09866  -0.0131   1.0000   0.0200
  -8.500  -0.4842   0.08481   0.07996  -0.0236   1.0000   0.0156
  -8.250  -0.4864   0.08046   0.07568  -0.0256   1.0000   0.0153
  -8.000  -0.4896   0.07633   0.07162  -0.0279   1.0000   0.0151
  -7.750  -0.4945   0.07150   0.06686  -0.0315   1.0000   0.0149
  -7.500  -0.4954   0.06622   0.06157  -0.0354   1.0000   0.0147
  -7.250  -0.4953   0.06114   0.05644  -0.0382   1.0000   0.0145
  -7.000  -0.4940   0.05638   0.05156  -0.0400   1.0000   0.0143
  -6.750  -0.4919   0.05161   0.04663  -0.0409   1.0000   0.0141
  -6.500  -0.4880   0.04722   0.04202  -0.0410   1.0000   0.0139
  -6.250  -0.4819   0.04313   0.03764  -0.0405   1.0000   0.0137
  -6.000  -0.4735   0.03920   0.03334  -0.0396   1.0000   0.0135
  -5.750  -0.4626   0.03564   0.02937  -0.0383   1.0000   0.0134
  -5.500  -0.4494   0.03238   0.02565  -0.0368   1.0000   0.0133
  -5.250  -0.4337   0.02948   0.02227  -0.0353   1.0000   0.0133
  -5.000  -0.4160   0.02695   0.01919  -0.0337   1.0000   0.0134
  -4.750  -0.3966   0.02469   0.01650  -0.0322   1.0000   0.0137
  -4.500  -0.3762   0.02281   0.01427  -0.0307   1.0000   0.0143
  -4.250  -0.3552   0.02159   0.01278  -0.0293   1.0000   0.0155
  -4.000  -0.3355   0.02007   0.01118  -0.0282   1.0000   0.0192
  -3.750  -0.3145   0.01898   0.00995  -0.0270   1.0000   0.0226
  -3.500  -0.2933   0.01776   0.00854  -0.0256   1.0000   0.0263
  -3.250  -0.2720   0.01677   0.00755  -0.0246   1.0000   0.0419
  -3.000  -0.2410   0.01554   0.00654  -0.0255   0.9962   0.0920
  -2.750  -0.2086   0.01452   0.00607  -0.0271   0.9911   0.2150
  -2.500  -0.1769   0.01366   0.00579  -0.0285   0.9855   0.3765
  -2.250  -0.1446   0.01304   0.00568  -0.0296   0.9803   0.5278
  -2.000  -0.1156   0.01258   0.00563  -0.0294   0.9737   0.6649
  -1.750  -0.0826   0.01229   0.00563  -0.0295   0.9689   0.7956
  -1.500  -0.0314   0.01215   0.00552  -0.0334   0.9668   0.9239
  -1.250   0.0252   0.01210   0.00522  -0.0394   0.9637   1.0000
  -1.000   0.0653   0.01213   0.00506  -0.0421   0.9566   1.0000
  -0.750   0.1022   0.01214   0.00493  -0.0441   0.9479   1.0000
  -0.500   0.1424   0.01214   0.00476  -0.0467   0.9405   1.0000
  -0.250   0.1768   0.01214   0.00467  -0.0481   0.9304   1.0000
   0.000   0.2098   0.01214   0.00459  -0.0491   0.9196   1.0000
   0.250   0.2427   0.01213   0.00452  -0.0500   0.9086   1.0000
   0.500   0.2747   0.01210   0.00446  -0.0507   0.8967   1.0000
   0.750   0.3049   0.01208   0.00440  -0.0509   0.8833   1.0000
   1.000   0.3334   0.01205   0.00434  -0.0507   0.8683   1.0000
   1.250   0.3612   0.01202   0.00430  -0.0503   0.8521   1.0000
   1.500   0.3888   0.01199   0.00425  -0.0498   0.8353   1.0000
   1.750   0.4144   0.01199   0.00427  -0.0489   0.8157   1.0000
   2.000   0.4407   0.01198   0.00425  -0.0482   0.7953   1.0000
   2.250   0.4660   0.01200   0.00426  -0.0472   0.7718   1.0000
   2.500   0.4916   0.01203   0.00428  -0.0463   0.7460   1.0000
   2.750   0.5170   0.01209   0.00437  -0.0453   0.7171   1.0000
   3.000   0.5421   0.01219   0.00442  -0.0443   0.6847   1.0000
   3.250   0.5668   0.01235   0.00451  -0.0432   0.6487   1.0000
   3.500   0.5911   0.01258   0.00464  -0.0421   0.6097   1.0000
   3.750   0.6149   0.01288   0.00483  -0.0410   0.5688   1.0000
   4.000   0.6382   0.01323   0.00513  -0.0399   0.5263   1.0000
   4.250   0.6612   0.01364   0.00543  -0.0388   0.4821   1.0000
   4.500   0.6838   0.01410   0.00577  -0.0377   0.4368   1.0000
   4.750   0.7061   0.01463   0.00616  -0.0367   0.3913   1.0000
   5.000   0.7283   0.01519   0.00661  -0.0357   0.3461   1.0000
   5.250   0.7502   0.01581   0.00711  -0.0348   0.3019   1.0000
   5.500   0.7718   0.01648   0.00767  -0.0338   0.2588   1.0000
   5.750   0.7934   0.01720   0.00829  -0.0329   0.2184   1.0000
   6.000   0.8147   0.01799   0.00909  -0.0320   0.1789   1.0000
   6.250   0.8356   0.01886   0.00985  -0.0312   0.1406   1.0000
   6.500   0.8559   0.01985   0.01072  -0.0302   0.1049   1.0000
   6.750   0.8756   0.02096   0.01177  -0.0292   0.0779   1.0000
   7.000   0.8944   0.02220   0.01292  -0.0280   0.0562   1.0000
   7.250   0.9122   0.02363   0.01441  -0.0266   0.0446   1.0000
   7.500   0.9293   0.02516   0.01609  -0.0250   0.0371   1.0000
   7.750   0.9466   0.02671   0.01780  -0.0235   0.0296   1.0000
   8.000   0.9598   0.02895   0.02008  -0.0218   0.0241   1.0000
   8.250   0.9786   0.03036   0.02181  -0.0205   0.0188   1.0000
   8.500   0.9924   0.03238   0.02398  -0.0190   0.0158   1.0000
   8.750   1.0032   0.03580   0.02766  -0.0171   0.0144   1.0000
   9.000   1.0167   0.03838   0.03078  -0.0154   0.0133   1.0000
   9.250   1.0268   0.04102   0.03383  -0.0136   0.0119   1.0000
   9.500   1.0333   0.04351   0.03668  -0.0118   0.0106   1.0000
   9.750   1.0363   0.04596   0.03942  -0.0099   0.0097   1.0000
  10.000   1.0348   0.04833   0.04202  -0.0079   0.0090   1.0000
  10.250   1.0264   0.05133   0.04529  -0.0054   0.0088   1.0000
  10.500   1.0152   0.05468   0.04889  -0.0037   0.0087   1.0000
  10.750   1.0011   0.05867   0.05317  -0.0031   0.0088   1.0000
  11.000   0.9848   0.06330   0.05804  -0.0038   0.0088   1.0000
  11.250   0.9668   0.06886   0.06382  -0.0062   0.0089   1.0000
  11.500   0.9462   0.07594   0.07110  -0.0107   0.0090   1.0000
  11.750   0.9235   0.08500   0.08036  -0.0172   0.0093   1.0000
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