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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 200,000
Max Cl/Cd: 85.16 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh38-il-200000-n5.txt
Download as CSV file: xf-mh38-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3411   0.08851   0.08514  -0.0402   1.0000   0.0073
  -8.750  -0.3422   0.08483   0.08152  -0.0415   1.0000   0.0073
  -8.500  -0.3459   0.08100   0.07776  -0.0426   1.0000   0.0073
  -8.250  -0.3501   0.07652   0.07338  -0.0448   0.9959   0.0073
  -8.000  -0.3393   0.06994   0.06681  -0.0531   0.9667   0.0071
  -7.750  -0.3291   0.06129   0.05815  -0.0654   0.9413   0.0070
  -7.500  -0.3226   0.04895   0.04572  -0.0815   0.9161   0.0067
  -7.250  -0.3260   0.03309   0.02901  -0.0939   0.8947   0.0064
  -7.000  -0.3122   0.02773   0.02292  -0.0959   0.8821   0.0065
  -6.750  -0.2929   0.02430   0.01886  -0.0964   0.8720   0.0068
  -6.500  -0.2709   0.02189   0.01595  -0.0963   0.8622   0.0072
  -6.250  -0.2468   0.02031   0.01392  -0.0961   0.8536   0.0078
  -6.000  -0.2229   0.01891   0.01229  -0.0961   0.8458   0.0096
  -5.750  -0.1972   0.01814   0.01132  -0.0960   0.8375   0.0116
  -5.500  -0.1716   0.01697   0.00986  -0.0956   0.8305   0.0132
  -5.250  -0.1463   0.01564   0.00832  -0.0954   0.8228   0.0160
  -5.000  -0.1196   0.01515   0.00768  -0.0952   0.8163   0.0219
  -4.750  -0.0932   0.01437   0.00679  -0.0950   0.8091   0.0303
  -4.500  -0.0664   0.01385   0.00618  -0.0949   0.8030   0.0411
  -4.250  -0.0394   0.01343   0.00567  -0.0948   0.7961   0.0538
  -4.000  -0.0123   0.01307   0.00523  -0.0946   0.7905   0.0670
  -3.750   0.0150   0.01278   0.00489  -0.0946   0.7837   0.0828
  -3.500   0.0424   0.01251   0.00454  -0.0945   0.7781   0.0973
  -3.250   0.0697   0.01226   0.00429  -0.0945   0.7719   0.1155
  -3.000   0.0971   0.01204   0.00405  -0.0944   0.7661   0.1358
  -2.750   0.1245   0.01183   0.00382  -0.0944   0.7606   0.1587
  -2.500   0.1520   0.01163   0.00364  -0.0944   0.7545   0.1840
  -2.250   0.1794   0.01144   0.00346  -0.0943   0.7497   0.2155
  -2.000   0.2068   0.01125   0.00335  -0.0944   0.7433   0.2524
  -1.750   0.2341   0.01106   0.00324  -0.0943   0.7380   0.2972
  -1.500   0.2613   0.01086   0.00315  -0.0943   0.7324   0.3516
  -1.250   0.2883   0.01066   0.00311  -0.0942   0.7267   0.4141
  -1.000   0.3150   0.01046   0.00307  -0.0940   0.7218   0.4834
  -0.750   0.3412   0.01024   0.00307  -0.0937   0.7156   0.5597
  -0.500   0.3663   0.01000   0.00307  -0.0930   0.7104   0.6477
  -0.250   0.3895   0.00973   0.00310  -0.0917   0.7047   0.7489
   0.000   0.4135   0.00945   0.00308  -0.0901   0.6991   0.8846
   0.250   0.4532   0.00938   0.00296  -0.0925   0.6938   1.0000
   0.500   0.4807   0.00946   0.00297  -0.0925   0.6875   1.0000
   0.750   0.5082   0.00954   0.00296  -0.0924   0.6822   1.0000
   1.000   0.5356   0.00963   0.00301  -0.0924   0.6757   1.0000
   1.250   0.5631   0.00973   0.00304  -0.0923   0.6699   1.0000
   1.500   0.5904   0.00982   0.00310  -0.0922   0.6636   1.0000
   1.750   0.6178   0.00992   0.00315  -0.0921   0.6572   1.0000
   2.000   0.6452   0.01002   0.00323  -0.0920   0.6508   1.0000
   2.250   0.6724   0.01013   0.00334  -0.0919   0.6439   1.0000
   2.500   0.6997   0.01024   0.00344  -0.0918   0.6370   1.0000
   2.750   0.7268   0.01034   0.00354  -0.0917   0.6297   1.0000
   3.000   0.7539   0.01046   0.00366  -0.0916   0.6219   1.0000
   3.250   0.7809   0.01057   0.00379  -0.0914   0.6142   1.0000
   3.500   0.8077   0.01069   0.00395  -0.0912   0.6049   1.0000
   3.750   0.8345   0.01082   0.00410  -0.0910   0.5960   1.0000
   4.000   0.8611   0.01095   0.00423  -0.0908   0.5867   1.0000
   4.250   0.8876   0.01109   0.00443  -0.0905   0.5760   1.0000
   4.500   0.9139   0.01124   0.00466  -0.0902   0.5649   1.0000
   4.750   0.9401   0.01139   0.00486  -0.0899   0.5529   1.0000
   5.000   0.9659   0.01156   0.00508  -0.0896   0.5395   1.0000
   5.250   0.9914   0.01175   0.00531  -0.0891   0.5242   1.0000
   5.500   1.0164   0.01197   0.00554  -0.0886   0.5063   1.0000
   5.750   1.0407   0.01222   0.00586  -0.0880   0.4835   1.0000
   6.000   1.0634   0.01257   0.00615  -0.0871   0.4530   1.0000
   6.250   1.0836   0.01309   0.00650  -0.0858   0.4088   1.0000
   6.500   1.1016   0.01380   0.00700  -0.0844   0.3566   1.0000
   6.750   1.1186   0.01463   0.00761  -0.0829   0.3050   1.0000
   7.000   1.1324   0.01572   0.00839  -0.0810   0.2433   1.0000
   7.250   1.1429   0.01708   0.00935  -0.0789   0.1734   1.0000
   7.500   1.1505   0.01867   0.01048  -0.0764   0.1031   1.0000
   7.750   1.1581   0.02020   0.01167  -0.0740   0.0543   1.0000
   8.000   1.1668   0.02157   0.01287  -0.0715   0.0294   1.0000
   8.250   1.1754   0.02280   0.01415  -0.0689   0.0181   1.0000
   8.500   1.1830   0.02397   0.01539  -0.0662   0.0133   1.0000
   8.750   1.1898   0.02523   0.01674  -0.0636   0.0104   1.0000
   9.000   1.1983   0.02641   0.01804  -0.0614   0.0086   1.0000
   9.250   1.2048   0.02781   0.01956  -0.0591   0.0078   1.0000
   9.500   1.2081   0.02954   0.02141  -0.0568   0.0071   1.0000
   9.750   1.2076   0.03170   0.02372  -0.0544   0.0066   1.0000
  10.000   1.2085   0.03390   0.02605  -0.0524   0.0063   1.0000
  10.250   1.2136   0.03584   0.02812  -0.0508   0.0061   1.0000
  10.500   1.2184   0.03792   0.03034  -0.0493   0.0060   1.0000
  10.750   1.2235   0.04012   0.03269  -0.0479   0.0057   1.0000
  11.000   1.2294   0.04235   0.03507  -0.0466   0.0056   1.0000
  11.250   1.2356   0.04472   0.03761  -0.0453   0.0054   1.0000
  11.500   1.2417   0.04725   0.04032  -0.0441   0.0053   1.0000
  11.750   1.2471   0.04992   0.04319  -0.0430   0.0053   1.0000
  12.000   1.2508   0.05285   0.04641  -0.0421   0.0052   1.0000
  12.250   1.2522   0.05605   0.04984  -0.0413   0.0051   1.0000
  12.500   1.2506   0.05967   0.05372  -0.0407   0.0050   1.0000
  12.750   1.2466   0.06357   0.05787  -0.0405   0.0050   1.0000
  13.000   1.2401   0.06779   0.06235  -0.0406   0.0050   1.0000
  13.250   1.2314   0.07236   0.06716  -0.0412   0.0049   1.0000
  13.500   1.2217   0.07719   0.07223  -0.0422   0.0048   1.0000
  13.750   1.2103   0.08248   0.07774  -0.0437   0.0048   1.0000
  14.000   1.1988   0.08801   0.08347  -0.0458   0.0046   1.0000
  14.250   1.1837   0.09463   0.09033  -0.0486   0.0047   1.0000
  14.500   1.1684   0.10168   0.09760  -0.0520   0.0047   1.0000
  14.750   1.1540   0.10893   0.10503  -0.0559   0.0046   1.0000
  15.000   1.1345   0.11800   0.11433  -0.0611   0.0048   1.0000
  15.250   1.1157   0.12758   0.12410  -0.0670   0.0049   1.0000
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