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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.27 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe144-il-1000000.txt
Download as CSV file: xf-goe144-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2756   0.10465   0.10312  -0.0256   1.0000   0.0121
 -10.000  -0.2738   0.10142   0.09989  -0.0258   1.0000   0.0128
  -8.250  -0.4519   0.02002   0.01705  -0.0951   0.9843   0.0099
  -8.000  -0.4241   0.01836   0.01517  -0.0962   0.9816   0.0102
  -7.750  -0.3994   0.01540   0.01177  -0.0972   0.9775   0.0110
  -7.500  -0.3679   0.01478   0.01108  -0.0983   0.9753   0.0117
  -7.250  -0.3359   0.01411   0.01031  -0.0995   0.9736   0.0123
  -7.000  -0.3032   0.01342   0.00951  -0.1007   0.9722   0.0130
  -6.750  -0.2719   0.01280   0.00877  -0.1015   0.9699   0.0138
  -6.500  -0.2444   0.01240   0.00828  -0.1014   0.9648   0.0142
  -6.250  -0.2139   0.01115   0.00687  -0.1023   0.9615   0.0157
  -6.000  -0.1797   0.01086   0.00653  -0.1036   0.9589   0.0168
  -5.750  -0.1489   0.01062   0.00625  -0.1041   0.9543   0.0181
  -5.500  -0.1167   0.01055   0.00614  -0.1049   0.9493   0.0190
  -5.250  -0.0841   0.00946   0.00490  -0.1061   0.9447   0.0211
  -5.000  -0.0535   0.00916   0.00454  -0.1066   0.9378   0.0226
  -4.750  -0.0209   0.00888   0.00419  -0.1075   0.9311   0.0243
  -4.500   0.0087   0.00876   0.00402  -0.1077   0.9228   0.0255
  -4.250   0.0377   0.00821   0.00332  -0.1078   0.9147   0.0273
  -4.000   0.0646   0.00781   0.00283  -0.1074   0.9056   0.0295
  -3.750   0.0919   0.00758   0.00253  -0.1072   0.8964   0.0315
  -3.500   0.1192   0.00740   0.00227  -0.1068   0.8863   0.0330
  -3.250   0.1456   0.00723   0.00203  -0.1063   0.8748   0.0341
  -3.000   0.1720   0.00708   0.00180  -0.1057   0.8609   0.0356
  -2.750   0.1979   0.00690   0.00156  -0.1050   0.8415   0.0396
  -2.500   0.2222   0.00679   0.00138  -0.1040   0.8015   0.0486
  -2.250   0.2440   0.00695   0.00133  -0.1024   0.7414   0.0665
  -2.000   0.2679   0.00708   0.00130  -0.1014   0.7060   0.0734
  -1.750   0.2931   0.00718   0.00128  -0.1007   0.6806   0.0778
  -1.500   0.3189   0.00726   0.00125  -0.1001   0.6591   0.0801
  -1.250   0.3448   0.00730   0.00119  -0.0995   0.6403   0.0826
  -1.000   0.3709   0.00730   0.00114  -0.0990   0.6214   0.0866
  -0.750   0.3970   0.00732   0.00110  -0.0985   0.6023   0.0894
  -0.500   0.4232   0.00736   0.00106  -0.0980   0.5852   0.0918
  -0.250   0.4497   0.00738   0.00104  -0.0976   0.5718   0.0952
   0.000   0.4762   0.00739   0.00103  -0.0972   0.5585   0.1027
   0.250   0.5024   0.00742   0.00107  -0.0968   0.5432   0.1193
   0.500   0.5290   0.00748   0.00111  -0.0964   0.5303   0.1349
   0.750   0.5557   0.00753   0.00115  -0.0961   0.5200   0.1466
   1.000   0.5823   0.00758   0.00119  -0.0957   0.5096   0.1542
   1.250   0.6091   0.00763   0.00123  -0.0954   0.4989   0.1597
   1.500   0.6357   0.00770   0.00126  -0.0950   0.4871   0.1636
   1.750   0.6622   0.00776   0.00130  -0.0947   0.4763   0.1686
   2.000   0.6888   0.00782   0.00134  -0.0943   0.4663   0.1729
   2.250   0.7155   0.00788   0.00140  -0.0940   0.4557   0.1767
   2.500   0.7419   0.00794   0.00146  -0.0936   0.4445   0.1834
   2.750   0.7682   0.00802   0.00153  -0.0932   0.4331   0.1910
   3.000   0.7943   0.00809   0.00162  -0.0929   0.4206   0.2098
   3.250   0.8205   0.00812   0.00174  -0.0925   0.4090   0.2538
   3.500   0.8465   0.00814   0.00185  -0.0921   0.3969   0.3088
   3.750   0.8819   0.00704   0.00212  -0.0943   0.3747   1.0000
   4.000   0.9059   0.00733   0.00226  -0.0935   0.3415   1.0000
   4.250   0.9302   0.00761   0.00241  -0.0928   0.3149   1.0000
   4.500   0.9536   0.00797   0.00261  -0.0920   0.2817   1.0000
   4.750   0.9765   0.00839   0.00285  -0.0911   0.2486   1.0000
   5.000   0.9996   0.00879   0.00310  -0.0902   0.2196   1.0000
   5.250   1.0230   0.00916   0.00335  -0.0894   0.1941   1.0000
   5.500   1.0425   0.00993   0.00377  -0.0881   0.1302   1.0000
   5.750   1.0622   0.01068   0.00427  -0.0867   0.0889   1.0000
   6.000   1.0790   0.01172   0.00495  -0.0849   0.0254   1.0000
   6.250   1.1016   0.01218   0.00542  -0.0838   0.0170   1.0000
   6.500   1.1253   0.01252   0.00580  -0.0830   0.0157   1.0000
   6.750   1.1481   0.01293   0.00625  -0.0821   0.0142   1.0000
   7.000   1.1694   0.01349   0.00687  -0.0809   0.0125   1.0000
   7.250   1.1905   0.01405   0.00751  -0.0796   0.0117   1.0000
   7.500   1.2126   0.01448   0.00799  -0.0786   0.0112   1.0000
   7.750   1.2338   0.01499   0.00855  -0.0775   0.0107   1.0000
   8.000   1.2543   0.01554   0.00915  -0.0762   0.0101   1.0000
   8.250   1.2741   0.01612   0.00977  -0.0749   0.0095   1.0000
   8.500   1.2921   0.01683   0.01053  -0.0733   0.0090   1.0000
   8.750   1.2975   0.01852   0.01238  -0.0696   0.0083   1.0000
   9.000   1.3170   0.01899   0.01290  -0.0683   0.0081   1.0000
   9.250   1.3337   0.01965   0.01361  -0.0665   0.0078   1.0000
   9.500   1.3483   0.02042   0.01444  -0.0644   0.0076   1.0000
   9.750   1.3598   0.02124   0.01534  -0.0619   0.0073   1.0000
  10.000   1.3673   0.02216   0.01633  -0.0586   0.0071   1.0000
  10.250   1.3744   0.02312   0.01735  -0.0554   0.0070   1.0000
  10.500   1.3835   0.02398   0.01828  -0.0527   0.0067   1.0000
  10.750   1.3894   0.02509   0.01947  -0.0497   0.0066   1.0000
  11.000   1.3938   0.02638   0.02083  -0.0468   0.0065   1.0000
  11.250   1.4033   0.02726   0.02176  -0.0448   0.0062   1.0000
  11.500   1.4053   0.02885   0.02344  -0.0421   0.0061   1.0000
  11.750   1.4076   0.03053   0.02519  -0.0397   0.0060   1.0000
  12.000   1.4049   0.03282   0.02754  -0.0372   0.0057   1.0000
  12.250   1.3999   0.03606   0.03090  -0.0347   0.0056   1.0000
  12.500   1.4004   0.03851   0.03349  -0.0330   0.0054   1.0000
  12.750   1.4039   0.04020   0.03529  -0.0319   0.0054   1.0000
  13.000   1.4074   0.04207   0.03728  -0.0311   0.0052   1.0000
  13.250   1.4065   0.04490   0.04025  -0.0302   0.0052   1.0000
  13.500   1.4065   0.04760   0.04307  -0.0298   0.0051   1.0000
  13.750   1.4041   0.05079   0.04640  -0.0295   0.0050   1.0000
  14.000   1.4006   0.05422   0.04998  -0.0294   0.0049   1.0000
  14.250   1.3949   0.05812   0.05402  -0.0296   0.0049   1.0000
  14.500   1.3874   0.06239   0.05845  -0.0302   0.0049   1.0000
  14.750   1.3800   0.06674   0.06295  -0.0312   0.0048   1.0000
  15.000   1.3674   0.07213   0.06852  -0.0325   0.0048   1.0000
  15.250   1.3558   0.07754   0.07409  -0.0344   0.0048   1.0000
  15.500   1.3447   0.08305   0.07975  -0.0367   0.0048   1.0000
  15.750   1.3290   0.08964   0.08651  -0.0396   0.0049   1.0000
  16.000   1.3150   0.09620   0.09323  -0.0428   0.0048   1.0000
  16.250   1.2998   0.10334   0.10052  -0.0466   0.0048   1.0000
  16.500   1.2855   0.11052   0.10784  -0.0506   0.0048   1.0000
  16.750   1.2693   0.11849   0.11596  -0.0552   0.0048   1.0000
  17.000   1.2527   0.12684   0.12445  -0.0602   0.0049   1.0000
  17.250   1.2343   0.13602   0.13377  -0.0659   0.0050   1.0000
  17.500   1.2172   0.14525   0.14314  -0.0717   0.0050   1.0000
  17.750   1.2030   0.15419   0.15220  -0.0775   0.0050   1.0000
  18.000   1.1856   0.16426   0.16239  -0.0839   0.0051   1.0000
  18.250   1.1673   0.17513   0.17336  -0.0909   0.0052   1.0000
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