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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 200,000
Max Cl/Cd: 67.05 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh30-il-200000.txt
Download as CSV file: xf-mh30-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4858   0.08492   0.08161  -0.0311   1.0000   0.0371
  -8.000  -0.4888   0.08004   0.07673  -0.0359   1.0000   0.0371
  -7.750  -0.4985   0.07292   0.06967  -0.0377   1.0000   0.0381
  -7.500  -0.4933   0.07039   0.06719  -0.0356   1.0000   0.0391
  -7.250  -0.4891   0.06717   0.06397  -0.0361   1.0000   0.0401
  -7.000  -0.4851   0.06361   0.06039  -0.0374   1.0000   0.0412
  -6.750  -0.4818   0.05976   0.05650  -0.0386   1.0000   0.0426
  -6.500  -0.4785   0.05584   0.05243  -0.0395   1.0000   0.0444
  -6.250  -0.4747   0.05175   0.04816  -0.0400   1.0000   0.0472
  -6.000  -0.4776   0.04703   0.04289  -0.0399   1.0000   0.0510
  -5.750  -0.4688   0.04380   0.03973  -0.0384   1.0000   0.0525
  -5.500  -0.4590   0.04149   0.03740  -0.0368   1.0000   0.0546
  -5.250  -0.4482   0.03892   0.03463  -0.0353   1.0000   0.0581
  -5.000  -0.4379   0.03569   0.03099  -0.0341   1.0000   0.0653
  -4.750  -0.4128   0.02777   0.02184  -0.0304   1.0000   0.0259
  -4.500  -0.3953   0.02394   0.01773  -0.0291   1.0000   0.0225
  -4.250  -0.3745   0.02121   0.01455  -0.0276   1.0000   0.0207
  -4.000  -0.3517   0.01898   0.01190  -0.0262   1.0000   0.0196
  -3.750  -0.3287   0.01732   0.00999  -0.0249   1.0000   0.0193
  -3.500  -0.3058   0.01603   0.00856  -0.0237   1.0000   0.0198
  -3.250  -0.2834   0.01499   0.00743  -0.0225   1.0000   0.0214
  -3.000  -0.2612   0.01419   0.00652  -0.0215   1.0000   0.0237
  -2.750  -0.2332   0.01246   0.00511  -0.0216   0.9986   0.0935
  -2.500  -0.1984   0.01119   0.00487  -0.0241   0.9944   0.3314
  -2.250  -0.1651   0.01049   0.00486  -0.0256   0.9888   0.5147
  -2.000  -0.1342   0.00987   0.00504  -0.0259   0.9832   0.7213
  -1.750  -0.0999   0.00958   0.00514  -0.0261   0.9785   0.8753
  -1.500  -0.0228   0.00951   0.00494  -0.0360   0.9814   1.0000
  -1.250   0.0168   0.00954   0.00478  -0.0387   0.9738   1.0000
  -1.000   0.0640   0.00960   0.00468  -0.0429   0.9690   1.0000
  -0.750   0.1031   0.00960   0.00457  -0.0453   0.9610   1.0000
  -0.500   0.1516   0.00956   0.00443  -0.0496   0.9563   1.0000
  -0.250   0.1936   0.00950   0.00429  -0.0525   0.9486   1.0000
   0.000   0.2413   0.00935   0.00410  -0.0564   0.9428   1.0000
   0.250   0.2775   0.00922   0.00395  -0.0579   0.9322   1.0000
   0.500   0.3112   0.00909   0.00380  -0.0587   0.9212   1.0000
   0.750   0.3410   0.00898   0.00366  -0.0586   0.9091   1.0000
   1.000   0.3673   0.00889   0.00354  -0.0578   0.8956   1.0000
   1.250   0.3916   0.00880   0.00344  -0.0565   0.8807   1.0000
   1.500   0.4152   0.00873   0.00336  -0.0551   0.8649   1.0000
   1.750   0.4389   0.00865   0.00326  -0.0536   0.8482   1.0000
   2.000   0.4618   0.00863   0.00321  -0.0521   0.8281   1.0000
   2.250   0.4857   0.00859   0.00314  -0.0507   0.8076   1.0000
   2.500   0.5094   0.00860   0.00312  -0.0494   0.7826   1.0000
   2.750   0.5333   0.00863   0.00315  -0.0481   0.7551   1.0000
   3.000   0.5573   0.00872   0.00317  -0.0469   0.7236   1.0000
   3.250   0.5812   0.00886   0.00321  -0.0457   0.6880   1.0000
   3.500   0.6048   0.00908   0.00330  -0.0445   0.6486   1.0000
   3.750   0.6280   0.00937   0.00344  -0.0433   0.6064   1.0000
   4.000   0.6511   0.00971   0.00368  -0.0422   0.5610   1.0000
   4.250   0.6738   0.01010   0.00391  -0.0411   0.5137   1.0000
   4.500   0.6962   0.01053   0.00418  -0.0400   0.4637   1.0000
   4.750   0.7183   0.01103   0.00450  -0.0390   0.4122   1.0000
   5.000   0.7403   0.01158   0.00486  -0.0380   0.3613   1.0000
   5.250   0.7623   0.01216   0.00527  -0.0370   0.3120   1.0000
   5.500   0.7841   0.01279   0.00574  -0.0361   0.2626   1.0000
   5.750   0.8056   0.01350   0.00633  -0.0353   0.2151   1.0000
   6.000   0.8272   0.01423   0.00689  -0.0344   0.1677   1.0000
   6.250   0.8479   0.01512   0.00755  -0.0335   0.1232   1.0000
   6.500   0.8673   0.01626   0.00848  -0.0324   0.0841   1.0000
   6.750   0.8850   0.01773   0.00985  -0.0307   0.0578   1.0000
   7.000   0.9035   0.01915   0.01132  -0.0292   0.0444   1.0000
   7.250   0.9223   0.02049   0.01270  -0.0278   0.0332   1.0000
   7.500   0.9416   0.02169   0.01398  -0.0267   0.0200   1.0000
   7.750   0.9573   0.02373   0.01610  -0.0249   0.0158   1.0000
   8.000   0.9729   0.02696   0.01959  -0.0229   0.0140   1.0000
   8.250   0.9912   0.02942   0.02237  -0.0214   0.0134   1.0000
   8.500   1.0070   0.03238   0.02571  -0.0196   0.0131   1.0000
   8.750   1.0187   0.03572   0.02947  -0.0176   0.0131   1.0000
   9.000   1.0253   0.03943   0.03363  -0.0153   0.0132   1.0000
   9.250   1.0265   0.04335   0.03807  -0.0128   0.0134   1.0000
   9.500   1.0217   0.04746   0.04256  -0.0102   0.0137   1.0000
   9.750   1.0112   0.05149   0.04691  -0.0075   0.0139   1.0000
  10.000   0.9950   0.05501   0.05067  -0.0045   0.0140   1.0000
  10.250   0.9758   0.05894   0.05480  -0.0027   0.0142   1.0000
  10.500   0.9565   0.06329   0.05933  -0.0025   0.0143   1.0000
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