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MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 100,000
Max Cl/Cd: 53.44 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh200-il-100000.txt
Download as CSV file: xf-mh200-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 200  12.97%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3314   0.09725   0.09307  -0.0413   1.0000   0.1276
  -9.500  -0.3548   0.09540   0.09133  -0.0399   1.0000   0.1317
  -9.250  -0.4178   0.09338   0.08949  -0.0415   1.0000   0.1338
  -9.000  -0.4885   0.09097   0.08674  -0.0499   1.0000   0.1335
  -8.750  -0.4554   0.08803   0.08380  -0.0446   1.0000   0.1372
  -8.500  -0.4666   0.08658   0.08244  -0.0410   1.0000   0.1395
  -8.250  -0.4913   0.08511   0.08107  -0.0378   1.0000   0.1415
  -8.000  -0.5266   0.08337   0.07945  -0.0351   1.0000   0.1430
  -7.750  -0.5643   0.08174   0.07790  -0.0321   1.0000   0.1433
  -7.500  -0.6126   0.07927   0.07541  -0.0311   1.0000   0.1464
  -6.250  -0.6577   0.04897   0.04289  -0.0277   1.0000   0.0643
  -6.000  -0.6349   0.04301   0.03622  -0.0277   0.9978   0.0513
  -5.750  -0.6086   0.03881   0.03158  -0.0287   0.9949   0.0475
  -5.500  -0.5795   0.03509   0.02699  -0.0289   0.9920   0.0436
  -5.250  -0.5498   0.03301   0.02439  -0.0291   0.9889   0.0425
  -5.000  -0.5197   0.03091   0.02212  -0.0300   0.9858   0.0441
  -4.500  -0.4596   0.02820   0.01910  -0.0310   0.9794   0.0505
  -4.250  -0.4308   0.02710   0.01785  -0.0310   0.9758   0.0529
  -4.000  -0.4016   0.02561   0.01650  -0.0317   0.9726   0.0627
  -3.750  -0.3704   0.02436   0.01534  -0.0328   0.9695   0.0830
  -3.500  -0.3575   0.02042   0.01425  -0.0315   0.9666   0.5115
  -3.250  -0.3457   0.02096   0.01547  -0.0264   0.9617   0.6907
  -3.000  -0.3282   0.02226   0.01674  -0.0222   0.9572   0.7621
  -2.750  -0.3206   0.02298   0.01739  -0.0167   0.9519   0.7996
  -2.500  -0.3082   0.02356   0.01784  -0.0123   0.9468   0.8280
  -2.250  -0.2882   0.02418   0.01832  -0.0094   0.9423   0.8531
  -2.000  -0.2812   0.02424   0.01827  -0.0048   0.9364   0.8753
  -1.750  -0.2605   0.02452   0.01841  -0.0026   0.9312   0.8979
  -1.500  -0.2313   0.02485   0.01857  -0.0024   0.9264   0.9184
  -1.250  -0.1932   0.02515   0.01867  -0.0042   0.9211   0.9365
  -1.000  -0.1277   0.02574   0.01904  -0.0116   0.9174   0.9505
  -0.750  -0.0433   0.02640   0.01945  -0.0227   0.9148   0.9610
  -0.500   0.0183   0.02671   0.01961  -0.0300   0.9101   0.9715
  -0.250   0.0806   0.02691   0.01967  -0.0377   0.9052   0.9795
   0.000   0.1450   0.02705   0.01971  -0.0455   0.9012   0.9858
   0.250   0.1931   0.02717   0.01975  -0.0507   0.8947   0.9931
   0.500   0.2490   0.02720   0.01973  -0.0571   0.8891   0.9992
   0.750   0.2770   0.02730   0.01980  -0.0582   0.8815   1.0000
   1.000   0.3018   0.02736   0.01984  -0.0586   0.8731   1.0000
   1.250   0.3122   0.02753   0.02000  -0.0565   0.8627   1.0000
   1.500   0.3573   0.02745   0.01992  -0.0600   0.8569   1.0000
   1.750   0.3617   0.02764   0.02012  -0.0567   0.8451   1.0000
   2.000   0.3753   0.02777   0.02025  -0.0549   0.8344   1.0000
   2.250   0.4245   0.02754   0.02004  -0.0587   0.8283   1.0000
   2.500   0.4309   0.02766   0.02018  -0.0554   0.8159   1.0000
   2.750   0.4449   0.02769   0.02023  -0.0534   0.8043   1.0000
   3.000   0.5114   0.02704   0.01968  -0.0594   0.7995   1.0000
   3.250   0.5222   0.02698   0.01965  -0.0565   0.7868   1.0000
   3.500   0.5388   0.02681   0.01953  -0.0544   0.7748   1.0000
   3.750   0.6189   0.02554   0.01842  -0.0620   0.7708   1.0000
   4.000   0.6322   0.02531   0.01825  -0.0592   0.7582   1.0000
   4.250   0.6527   0.02489   0.01790  -0.0573   0.7462   1.0000
   4.500   0.7229   0.02334   0.01653  -0.0628   0.7411   1.0000
   4.750   0.7402   0.02287   0.01614  -0.0603   0.7278   1.0000
   5.000   0.7618   0.02226   0.01564  -0.0583   0.7145   1.0000
   5.250   0.7886   0.02150   0.01498  -0.0571   0.7006   1.0000
   5.500   0.8196   0.02061   0.01420  -0.0565   0.6856   1.0000
   5.750   0.8539   0.01963   0.01333  -0.0563   0.6689   1.0000
   6.000   0.8700   0.01922   0.01303  -0.0536   0.6457   1.0000
   6.250   0.8956   0.01858   0.01246  -0.0523   0.6191   1.0000
   6.500   0.9234   0.01799   0.01187  -0.0513   0.5851   1.0000
   6.750   0.9481   0.01779   0.01153  -0.0500   0.5414   1.0000
   7.000   0.9668   0.01809   0.01163  -0.0480   0.4909   1.0000
   7.250   0.9828   0.01872   0.01196  -0.0459   0.4408   1.0000
   7.500   0.9956   0.01956   0.01253  -0.0436   0.3943   1.0000
   7.750   1.0074   0.02051   0.01321  -0.0412   0.3531   1.0000
   8.000   1.0184   0.02149   0.01403  -0.0389   0.3156   1.0000
   8.250   1.0285   0.02253   0.01486  -0.0365   0.2829   1.0000
   8.500   1.0377   0.02362   0.01577  -0.0340   0.2532   1.0000
   8.750   1.0464   0.02478   0.01682  -0.0315   0.2250   1.0000
   9.000   1.0550   0.02600   0.01795  -0.0292   0.1984   1.0000
   9.250   1.0637   0.02734   0.01920  -0.0270   0.1737   1.0000
   9.500   1.0728   0.02881   0.02053  -0.0250   0.1519   1.0000
   9.750   1.0832   0.03031   0.02200  -0.0231   0.1324   1.0000
  10.000   1.0948   0.03189   0.02349  -0.0215   0.1164   1.0000
  10.250   1.1115   0.03364   0.02520  -0.0205   0.1031   1.0000
  10.500   1.1279   0.03544   0.02707  -0.0194   0.0918   1.0000
  10.750   1.1483   0.03753   0.02928  -0.0189   0.0824   1.0000
  11.000   1.1746   0.04000   0.03169  -0.0192   0.0739   1.0000
  11.250   1.1823   0.04182   0.03384  -0.0171   0.0682   1.0000
  11.500   1.2071   0.04497   0.03700  -0.0175   0.0620   1.0000
  11.750   1.2074   0.04712   0.03956  -0.0147   0.0585   1.0000
  12.000   1.2127   0.04949   0.04214  -0.0130   0.0548   1.0000
  12.250   1.2257   0.05374   0.04646  -0.0126   0.0509   1.0000
  12.500   1.2119   0.05622   0.04936  -0.0094   0.0496   1.0000
  12.750   1.1988   0.05934   0.05285  -0.0069   0.0483   1.0000
  13.000   1.1850   0.06285   0.05670  -0.0051   0.0469   1.0000
  13.250   1.1694   0.06693   0.06108  -0.0038   0.0462   1.0000
  13.500   1.1504   0.07150   0.06595  -0.0031   0.0459   1.0000
  13.750   1.1284   0.07661   0.07135  -0.0032   0.0459   1.0000
  14.000   1.1032   0.08242   0.07743  -0.0042   0.0462   1.0000
  14.250   1.0757   0.08903   0.08429  -0.0064   0.0468   1.0000
  14.500   1.0472   0.09650   0.09197  -0.0098   0.0476   1.0000
  14.750   1.0189   0.10487   0.10051  -0.0145   0.0486   1.0000
  15.000   0.9920   0.11414   0.10990  -0.0200   0.0498   1.0000
  15.250   0.9704   0.12348   0.11930  -0.0255   0.0508   1.0000
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