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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 200,000
Max Cl/Cd: 59.84 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh30-il-200000-n5.txt
Download as CSV file: xf-mh30-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4835   0.08474   0.08129  -0.0207   1.0000   0.0112
  -8.250  -0.4867   0.08011   0.07672  -0.0231   1.0000   0.0108
  -8.000  -0.4911   0.07564   0.07231  -0.0257   1.0000   0.0104
  -7.750  -0.4996   0.07062   0.06736  -0.0293   1.0000   0.0101
  -7.500  -0.5029   0.06415   0.06089  -0.0352   1.0000   0.0097
  -7.250  -0.5063   0.05633   0.05297  -0.0400   1.0000   0.0091
  -7.000  -0.5077   0.04836   0.04476  -0.0420   1.0000   0.0083
  -6.750  -0.5028   0.04364   0.03979  -0.0416   1.0000   0.0080
  -6.500  -0.4952   0.04050   0.03642  -0.0404   1.0000   0.0078
  -6.000  -0.4774   0.03521   0.03059  -0.0372   1.0000   0.0075
  -5.750  -0.4703   0.03148   0.02649  -0.0354   1.0000   0.0074
  -5.500  -0.4474   0.02753   0.02200  -0.0361   0.9969   0.0073
  -5.250  -0.4179   0.02418   0.01810  -0.0374   0.9930   0.0072
  -5.000  -0.3885   0.02159   0.01498  -0.0381   0.9888   0.0072
  -4.750  -0.3571   0.01943   0.01242  -0.0390   0.9851   0.0073
  -4.500  -0.3241   0.01767   0.01037  -0.0401   0.9821   0.0074
  -4.250  -0.2935   0.01630   0.00881  -0.0407   0.9776   0.0075
  -4.000  -0.2629   0.01462   0.00693  -0.0413   0.9731   0.0084
  -3.750  -0.2285   0.01368   0.00582  -0.0427   0.9697   0.0102
  -3.500  -0.1962   0.01302   0.00503  -0.0436   0.9651   0.0172
  -3.250  -0.1662   0.01197   0.00441  -0.0445   0.9599   0.0847
  -3.000  -0.1329   0.01140   0.00398  -0.0459   0.9560   0.1517
  -2.750  -0.1041   0.01085   0.00373  -0.0464   0.9498   0.2378
  -2.500  -0.0743   0.01023   0.00353  -0.0472   0.9443   0.3531
  -2.250  -0.0454   0.00979   0.00336  -0.0475   0.9380   0.4428
  -2.000  -0.0175   0.00937   0.00324  -0.0474   0.9310   0.5362
  -1.750   0.0088   0.00901   0.00315  -0.0468   0.9234   0.6238
  -1.500   0.0357   0.00871   0.00305  -0.0462   0.9161   0.7030
  -1.250   0.0603   0.00848   0.00300  -0.0449   0.9071   0.7743
  -1.000   0.0888   0.00830   0.00293  -0.0443   0.8997   0.8404
  -0.750   0.1231   0.00819   0.00286  -0.0451   0.8912   0.8990
  -0.500   0.1664   0.00810   0.00273  -0.0480   0.8834   0.9436
  -0.250   0.2094   0.00802   0.00258  -0.0509   0.8745   0.9742
   0.000   0.2506   0.00796   0.00246  -0.0536   0.8623   0.9966
   0.250   0.2770   0.00794   0.00237  -0.0532   0.8475   1.0000
   0.500   0.3005   0.00795   0.00231  -0.0521   0.8310   1.0000
   0.750   0.3243   0.00797   0.00225  -0.0511   0.8135   1.0000
   1.000   0.3485   0.00800   0.00221  -0.0501   0.7949   1.0000
   1.250   0.3728   0.00805   0.00218  -0.0491   0.7733   1.0000
   1.500   0.3972   0.00811   0.00217  -0.0482   0.7494   1.0000
   1.750   0.4216   0.00820   0.00216  -0.0472   0.7221   1.0000
   2.000   0.4459   0.00833   0.00217  -0.0463   0.6917   1.0000
   2.250   0.4701   0.00851   0.00221  -0.0454   0.6586   1.0000
   2.500   0.4941   0.00872   0.00228  -0.0444   0.6232   1.0000
   2.750   0.5181   0.00897   0.00243  -0.0436   0.5866   1.0000
   3.000   0.5419   0.00925   0.00257  -0.0427   0.5494   1.0000
   3.250   0.5657   0.00956   0.00274  -0.0419   0.5113   1.0000
   3.500   0.5895   0.00989   0.00293  -0.0411   0.4719   1.0000
   3.750   0.6132   0.01025   0.00315  -0.0403   0.4317   1.0000
   4.000   0.6367   0.01064   0.00345  -0.0396   0.3915   1.0000
   4.250   0.6603   0.01105   0.00373  -0.0389   0.3518   1.0000
   4.500   0.6838   0.01149   0.00405  -0.0382   0.3120   1.0000
   4.750   0.7072   0.01196   0.00439  -0.0376   0.2735   1.0000
   5.000   0.7306   0.01245   0.00477  -0.0369   0.2377   1.0000
   5.250   0.7541   0.01294   0.00518  -0.0363   0.2050   1.0000
   5.500   0.7772   0.01349   0.00563  -0.0357   0.1709   1.0000
   5.750   0.8000   0.01411   0.00620  -0.0351   0.1370   1.0000
   6.000   0.8225   0.01477   0.00674  -0.0344   0.1040   1.0000
   6.250   0.8446   0.01548   0.00734  -0.0337   0.0750   1.0000
   6.500   0.8669   0.01620   0.00802  -0.0329   0.0553   1.0000
   6.750   0.8888   0.01697   0.00881  -0.0321   0.0406   1.0000
   7.000   0.9100   0.01789   0.00979  -0.0310   0.0309   1.0000
   7.250   0.9304   0.01887   0.01080  -0.0300   0.0223   1.0000
   7.500   0.9511   0.01977   0.01170  -0.0292   0.0136   1.0000
   7.750   0.9714   0.02071   0.01271  -0.0282   0.0089   1.0000
   8.000   0.9884   0.02220   0.01440  -0.0267   0.0065   1.0000
   8.250   1.0055   0.02361   0.01602  -0.0251   0.0056   1.0000
   8.500   1.0218   0.02511   0.01772  -0.0236   0.0050   1.0000
   8.750   1.0374   0.02668   0.01959  -0.0220   0.0046   1.0000
   9.000   1.0516   0.02843   0.02156  -0.0204   0.0044   1.0000
   9.250   1.0640   0.03038   0.02374  -0.0187   0.0042   1.0000
   9.500   1.0737   0.03265   0.02629  -0.0167   0.0040   1.0000
   9.750   1.0801   0.03522   0.02916  -0.0145   0.0039   1.0000
  10.000   1.0821   0.03803   0.03229  -0.0121   0.0038   1.0000
  10.250   1.0779   0.04085   0.03541  -0.0091   0.0038   1.0000
  10.500   1.0700   0.04373   0.03858  -0.0062   0.0037   1.0000
  10.750   1.0623   0.04659   0.04169  -0.0041   0.0038   1.0000
  11.000   1.0501   0.05011   0.04546  -0.0029   0.0038   1.0000
  11.250   1.0366   0.05409   0.04968  -0.0028   0.0038   1.0000
  11.500   1.0200   0.05905   0.05487  -0.0041   0.0037   1.0000
  11.750   1.0033   0.06483   0.06086  -0.0070   0.0038   1.0000
  12.000   0.9920   0.07062   0.06683  -0.0107   0.0038   1.0000
  12.250   0.9767   0.07811   0.07450  -0.0160   0.0039   1.0000
  12.500   0.9583   0.08735   0.08390  -0.0225   0.0039   1.0000
  12.750   0.9351   0.09912   0.09583  -0.0301   0.0041   1.0000
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