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MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 84 13.69% (mh84-il)
Reynolds number: 200,000
Max Cl/Cd: 66.28 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh84-il-200000-n5.txt
Download as CSV file: xf-mh84-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 84  13.69%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3170   0.07024   0.06639  -0.0278   0.7546   0.0179
  -8.000  -0.4061   0.04099   0.03664  -0.0591   0.7505   0.0169
  -7.750  -0.4000   0.03389   0.02880  -0.0664   0.7394   0.0169
  -7.500  -0.3816   0.03022   0.02461  -0.0688   0.7272   0.0169
  -7.250  -0.3596   0.02765   0.02159  -0.0700   0.7159   0.0171
  -7.000  -0.3355   0.02564   0.01919  -0.0706   0.7041   0.0173
  -6.750  -0.3100   0.02398   0.01719  -0.0710   0.6927   0.0176
  -6.500  -0.2839   0.02263   0.01552  -0.0711   0.6814   0.0179
  -6.250  -0.2573   0.02155   0.01430  -0.0711   0.6698   0.0182
  -6.000  -0.2306   0.02069   0.01330  -0.0711   0.6590   0.0186
  -5.750  -0.2031   0.01988   0.01237  -0.0711   0.6474   0.0191
  -5.500  -0.1756   0.01913   0.01145  -0.0710   0.6367   0.0197
  -5.250  -0.1476   0.01841   0.01057  -0.0709   0.6254   0.0204
  -5.000  -0.1195   0.01775   0.00977  -0.0708   0.6148   0.0212
  -4.750  -0.0913   0.01720   0.00913  -0.0708   0.6037   0.0221
  -4.500  -0.0627   0.01673   0.00854  -0.0708   0.5933   0.0238
  -4.250  -0.0342   0.01629   0.00800  -0.0707   0.5825   0.0257
  -4.000  -0.0053   0.01586   0.00746  -0.0706   0.5720   0.0283
  -3.750   0.0234   0.01546   0.00695  -0.0706   0.5619   0.0312
  -3.500   0.0525   0.01504   0.00648  -0.0705   0.5511   0.0354
  -3.250   0.0812   0.01468   0.00605  -0.0705   0.5414   0.0431
  -3.000   0.1103   0.01430   0.00570  -0.0705   0.5308   0.0562
  -2.750   0.1391   0.01401   0.00541  -0.0704   0.5211   0.0762
  -2.500   0.1680   0.01377   0.00522  -0.0704   0.5107   0.0996
  -2.250   0.1968   0.01361   0.00506  -0.0703   0.5012   0.1236
  -2.000   0.2258   0.01348   0.00495  -0.0702   0.4909   0.1470
  -1.750   0.2546   0.01339   0.00486  -0.0701   0.4816   0.1694
  -1.500   0.2835   0.01333   0.00479  -0.0700   0.4716   0.1911
  -1.250   0.3123   0.01330   0.00471  -0.0699   0.4625   0.2108
  -1.000   0.3412   0.01326   0.00465  -0.0698   0.4528   0.2291
  -0.750   0.3699   0.01324   0.00460  -0.0697   0.4440   0.2471
  -0.500   0.3988   0.01321   0.00456  -0.0696   0.4346   0.2655
  -0.250   0.4274   0.01321   0.00454  -0.0694   0.4260   0.2852
   0.000   0.4561   0.01320   0.00453  -0.0693   0.4168   0.3071
   0.250   0.4846   0.01322   0.00454  -0.0692   0.4086   0.3318
   0.500   0.5132   0.01320   0.00457  -0.0691   0.3997   0.3607
   1.000   0.5697   0.01318   0.00469  -0.0688   0.3835   0.4416
   1.500   0.6248   0.01310   0.00489  -0.0683   0.3678   0.5683
   1.750   0.6509   0.01302   0.00501  -0.0676   0.3601   0.6554
   2.000   0.6748   0.01285   0.00511  -0.0663   0.3535   0.7650
   2.250   0.7048   0.01265   0.00510  -0.0661   0.3457   1.0000
   2.500   0.7330   0.01289   0.00520  -0.0660   0.3388   1.0000
   2.750   0.7614   0.01309   0.00534  -0.0660   0.3314   1.0000
   3.000   0.7894   0.01335   0.00547  -0.0659   0.3247   1.0000
   3.250   0.8175   0.01358   0.00563  -0.0658   0.3184   1.0000
   3.500   0.8454   0.01382   0.00580  -0.0656   0.3115   1.0000
   3.750   0.8727   0.01412   0.00598  -0.0655   0.3054   1.0000
   4.000   0.9006   0.01435   0.00619  -0.0654   0.2991   1.0000
   4.250   0.9279   0.01464   0.00640  -0.0652   0.2931   1.0000
   4.500   0.9550   0.01495   0.00664  -0.0651   0.2877   1.0000
   4.750   0.9824   0.01522   0.00688  -0.0649   0.2817   1.0000
   5.000   1.0091   0.01554   0.00714  -0.0647   0.2761   1.0000
   5.250   1.0357   0.01587   0.00741  -0.0645   0.2713   1.0000
   5.500   1.0626   0.01617   0.00772  -0.0643   0.2659   1.0000
   5.750   1.0888   0.01652   0.00801  -0.0641   0.2607   1.0000
   6.000   1.1146   0.01691   0.00833  -0.0638   0.2562   1.0000
   6.250   1.1409   0.01723   0.00869  -0.0636   0.2515   1.0000
   6.500   1.1666   0.01760   0.00904  -0.0634   0.2469   1.0000
   6.750   1.1916   0.01802   0.00940  -0.0630   0.2427   1.0000
   7.000   1.2169   0.01841   0.00980  -0.0627   0.2385   1.0000
   7.250   1.2419   0.01880   0.01022  -0.0624   0.2342   1.0000
   7.500   1.2663   0.01923   0.01064  -0.0620   0.2304   1.0000
   7.750   1.2897   0.01973   0.01109  -0.0616   0.2269   1.0000
   8.000   1.3139   0.02016   0.01157  -0.0612   0.2232   1.0000
   8.250   1.3376   0.02060   0.01205  -0.0608   0.2193   1.0000
   8.500   1.3604   0.02110   0.01255  -0.0603   0.2157   1.0000
   8.750   1.3821   0.02166   0.01309  -0.0597   0.2127   1.0000
   9.000   1.4042   0.02220   0.01366  -0.0591   0.2097   1.0000
   9.250   1.4260   0.02272   0.01425  -0.0585   0.2064   1.0000
   9.500   1.4466   0.02328   0.01486  -0.0579   0.2031   1.0000
   9.750   1.4658   0.02391   0.01549  -0.0571   0.2001   1.0000
  10.000   1.4835   0.02463   0.01618  -0.0562   0.1975   1.0000
  10.250   1.5022   0.02525   0.01690  -0.0553   0.1948   1.0000
  10.500   1.5193   0.02594   0.01767  -0.0543   0.1921   1.0000
  10.750   1.5331   0.02667   0.01847  -0.0530   0.1896   1.0000
  11.000   1.5445   0.02752   0.01935  -0.0515   0.1872   1.0000
  11.250   1.5548   0.02850   0.02032  -0.0501   0.1849   1.0000
  11.500   1.5656   0.02954   0.02141  -0.0490   0.1827   1.0000
  11.750   1.5766   0.03062   0.02262  -0.0480   0.1803   1.0000
  12.000   1.5867   0.03182   0.02391  -0.0471   0.1780   1.0000
  12.250   1.5959   0.03312   0.02529  -0.0463   0.1759   1.0000
  12.500   1.6045   0.03453   0.02674  -0.0456   0.1739   1.0000
  12.750   1.6126   0.03603   0.02827  -0.0450   0.1721   1.0000
  13.000   1.6210   0.03759   0.02985  -0.0445   0.1702   1.0000
  13.250   1.6275   0.03937   0.03179  -0.0442   0.1681   1.0000
  13.500   1.6331   0.04128   0.03382  -0.0439   0.1660   1.0000
  13.750   1.6380   0.04331   0.03595  -0.0438   0.1639   1.0000
  14.000   1.6426   0.04539   0.03811  -0.0437   0.1621   1.0000
  14.250   1.6474   0.04750   0.04027  -0.0437   0.1604   1.0000
  14.500   1.6529   0.04953   0.04232  -0.0436   0.1588   1.0000
  14.750   1.6563   0.05191   0.04479  -0.0437   0.1572   1.0000
  15.000   1.6554   0.05486   0.04792  -0.0442   0.1554   1.0000
  15.250   1.6539   0.05791   0.05111  -0.0448   0.1535   1.0000
  15.500   1.6526   0.06102   0.05434  -0.0455   0.1517   1.0000
  15.750   1.6514   0.06418   0.05759  -0.0463   0.1499   1.0000
  16.000   1.6524   0.06712   0.06059  -0.0470   0.1484   1.0000
  16.250   1.6566   0.06962   0.06313  -0.0475   0.1470   1.0000
  16.500   1.6566   0.07283   0.06643  -0.0483   0.1455   1.0000
  16.750   1.6444   0.07796   0.07177  -0.0503   0.1437   1.0000
  17.000   1.6325   0.08316   0.07715  -0.0524   0.1419   1.0000
  17.250   1.6219   0.08827   0.08240  -0.0546   0.1400   1.0000
  17.500   1.6148   0.09293   0.08717  -0.0565   0.1383   1.0000
  17.750   1.6130   0.09672   0.09103  -0.0580   0.1368   1.0000
  18.000   1.6209   0.09883   0.09315  -0.0585   0.1354   1.0000
  18.250   1.6003   0.10599   0.10049  -0.0620   0.1336   1.0000
  18.500   1.5354   0.12157   0.11644  -0.0707   0.1305   1.0000
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