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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 500,000
Max Cl/Cd: 42.89 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe411-il-500000-n5.txt
Download as CSV file: xf-goe411-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6395   0.10953   0.10715  -0.0264   1.0000   0.0033
 -13.750  -0.6623   0.09910   0.09662  -0.0323   1.0000   0.0033
 -13.500  -0.6842   0.09000   0.08742  -0.0378   1.0000   0.0032
 -13.250  -0.7036   0.08238   0.07968  -0.0425   1.0000   0.0032
 -13.000  -0.7203   0.07601   0.07320  -0.0463   1.0000   0.0031
 -12.750  -0.7418   0.06942   0.06646  -0.0498   1.0000   0.0031
 -12.500  -0.7579   0.06433   0.06124  -0.0521   1.0000   0.0031
 -12.250  -0.7732   0.05988   0.05666  -0.0535   1.0000   0.0031
 -12.000  -0.7910   0.05558   0.05220  -0.0540   1.0000   0.0030
 -11.750  -0.8077   0.05190   0.04835  -0.0534   1.0000   0.0030
 -11.500  -0.8248   0.04850   0.04477  -0.0518   1.0000   0.0030
 -11.250  -0.8400   0.04557   0.04167  -0.0492   1.0000   0.0029
 -11.000  -0.8540   0.04299   0.03890  -0.0458   1.0000   0.0029
 -10.750  -0.8669   0.04074   0.03647  -0.0417   1.0000   0.0030
 -10.500  -0.8791   0.03863   0.03417  -0.0369   1.0000   0.0030
 -10.250  -0.8886   0.03708   0.03247  -0.0318   1.0000   0.0030
 -10.000  -0.9003   0.03513   0.03032  -0.0259   1.0000   0.0029
  -9.750  -0.9083   0.03365   0.02868  -0.0202   1.0000   0.0029
  -9.500  -0.9097   0.03194   0.02680  -0.0157   1.0000   0.0030
  -9.250  -0.9077   0.03024   0.02492  -0.0116   1.0000   0.0030
  -9.000  -0.9032   0.02852   0.02302  -0.0078   1.0000   0.0030
  -8.750  -0.8814   0.02635   0.02064  -0.0076   0.9985   0.0031
  -8.500  -0.8582   0.02465   0.01879  -0.0075   0.9968   0.0032
  -8.250  -0.8344   0.02312   0.01710  -0.0075   0.9950   0.0036
  -8.000  -0.8117   0.02174   0.01561  -0.0072   0.9928   0.0037
  -7.750  -0.7868   0.02056   0.01433  -0.0073   0.9899   0.0040
  -7.500  -0.7600   0.01929   0.01295  -0.0079   0.9871   0.0043
  -7.250  -0.7328   0.01853   0.01211  -0.0084   0.9837   0.0046
  -7.000  -0.7045   0.01795   0.01147  -0.0090   0.9801   0.0048
  -6.750  -0.6846   0.01617   0.00957  -0.0084   0.9769   0.0057
  -6.500  -0.6619   0.01561   0.00892  -0.0078   0.9715   0.0065
  -6.250  -0.6341   0.01488   0.00813  -0.0082   0.9686   0.0074
  -6.000  -0.6095   0.01425   0.00743  -0.0079   0.9639   0.0089
  -5.750  -0.5817   0.01370   0.00681  -0.0082   0.9597   0.0108
  -5.500  -0.5492   0.01333   0.00639  -0.0094   0.9572   0.0119
  -5.250  -0.5262   0.01290   0.00592  -0.0087   0.9507   0.0134
  -5.000  -0.4967   0.01239   0.00533  -0.0094   0.9473   0.0160
  -4.750  -0.4698   0.01205   0.00493  -0.0094   0.9418   0.0173
  -4.500  -0.4388   0.01174   0.00455  -0.0103   0.9369   0.0182
  -4.250  -0.4074   0.01147   0.00417  -0.0113   0.9323   0.0183
  -4.000  -0.3781   0.01123   0.00387  -0.0117   0.9254   0.0186
  -3.750  -0.3460   0.01100   0.00358  -0.0128   0.9194   0.0191
  -3.500  -0.3148   0.01078   0.00333  -0.0136   0.9114   0.0234
  -3.250  -0.2936   0.00984   0.00284  -0.0128   0.9008   0.1449
  -3.000  -0.2664   0.00933   0.00256  -0.0131   0.8903   0.2001
  -2.750  -0.2443   0.00860   0.00225  -0.0124   0.8778   0.3016
  -2.500  -0.2184   0.00826   0.00205  -0.0123   0.8644   0.3518
  -2.250  -0.1950   0.00793   0.00191  -0.0116   0.8498   0.4100
  -2.000  -0.1699   0.00778   0.00181  -0.0111   0.8343   0.4394
  -1.750  -0.1488   0.00755   0.00174  -0.0098   0.8180   0.4917
  -1.500  -0.1264   0.00742   0.00166  -0.0087   0.8017   0.5236
  -1.250  -0.1023   0.00739   0.00160  -0.0079   0.7837   0.5385
  -1.000  -0.0787   0.00737   0.00155  -0.0070   0.7620   0.5504
  -0.750  -0.0567   0.00736   0.00150  -0.0057   0.7354   0.5665
  -0.500  -0.0368   0.00737   0.00145  -0.0040   0.7013   0.5881
  -0.250  -0.0185   0.00738   0.00142  -0.0020   0.6661   0.6115
   0.000   0.0000   0.00738   0.00141   0.0000   0.6370   0.6372
   0.250   0.0185   0.00738   0.00142   0.0020   0.6116   0.6661
   0.500   0.0371   0.00738   0.00145   0.0040   0.5881   0.6989
   0.750   0.0568   0.00737   0.00150   0.0057   0.5663   0.7339
   1.000   0.0788   0.00737   0.00155   0.0070   0.5504   0.7616
   1.250   0.1023   0.00739   0.00160   0.0079   0.5384   0.7836
   1.500   0.1267   0.00741   0.00167   0.0086   0.5265   0.8016
   1.750   0.1473   0.00760   0.00173   0.0101   0.4803   0.8185
   2.000   0.1695   0.00779   0.00181   0.0112   0.4366   0.8344
   2.250   0.1940   0.00797   0.00191   0.0118   0.4014   0.8502
   2.500   0.2202   0.00817   0.00204   0.0120   0.3694   0.8641
   2.750   0.2445   0.00858   0.00225   0.0124   0.3044   0.8772
   3.000   0.2670   0.00929   0.00255   0.0130   0.2060   0.8901
   3.250   0.2932   0.00986   0.00285   0.0129   0.1419   0.9008
   3.500   0.3147   0.01078   0.00333   0.0137   0.0226   0.9113
   3.750   0.3460   0.01100   0.00358   0.0128   0.0191   0.9193
   4.000   0.3782   0.01123   0.00387   0.0117   0.0187   0.9253
   4.250   0.4074   0.01147   0.00417   0.0112   0.0183   0.9323
   4.500   0.4392   0.01174   0.00455   0.0102   0.0182   0.9370
   4.750   0.4700   0.01205   0.00493   0.0094   0.0173   0.9418
   5.000   0.4968   0.01238   0.00533   0.0094   0.0160   0.9473
   5.250   0.5260   0.01293   0.00594   0.0087   0.0130   0.9507
   5.500   0.5490   0.01335   0.00642   0.0095   0.0119   0.9573
   5.750   0.5819   0.01370   0.00681   0.0081   0.0107   0.9597
   6.000   0.6099   0.01422   0.00740   0.0078   0.0088   0.9638
   6.250   0.6342   0.01487   0.00813   0.0082   0.0079   0.9685
   6.500   0.6620   0.01560   0.00891   0.0078   0.0066   0.9715
   6.750   0.6838   0.01628   0.00970   0.0086   0.0061   0.9770
   7.000   0.7042   0.01798   0.01150   0.0090   0.0048   0.9802
   7.250   0.7327   0.01855   0.01213   0.0084   0.0046   0.9837
   7.500   0.7592   0.01945   0.01311   0.0080   0.0044   0.9872
   7.750   0.7884   0.02035   0.01411   0.0070   0.0039   0.9898
   8.000   0.8117   0.02179   0.01566   0.0072   0.0038   0.9928
   8.250   0.8346   0.02314   0.01711   0.0075   0.0036   0.9950
   8.500   0.8579   0.02477   0.01891   0.0076   0.0034   0.9967
   8.750   0.8816   0.02628   0.02057   0.0075   0.0031   0.9986
   9.000   0.9035   0.02834   0.02283   0.0078   0.0030   1.0000
   9.250   0.9080   0.02998   0.02463   0.0115   0.0030   1.0000
   9.500   0.9098   0.03175   0.02659   0.0157   0.0029   1.0000
   9.750   0.9086   0.03356   0.02858   0.0202   0.0029   1.0000
  10.000   0.9003   0.03519   0.03039   0.0259   0.0029   1.0000
  10.250   0.8908   0.03668   0.03203   0.0315   0.0029   1.0000
  10.500   0.8796   0.03853   0.03407   0.0368   0.0029   1.0000
  10.750   0.8670   0.04073   0.03646   0.0417   0.0030   1.0000
  11.000   0.8534   0.04310   0.03902   0.0459   0.0029   1.0000
  11.250   0.8425   0.04532   0.04140   0.0490   0.0030   1.0000
  11.500   0.8248   0.04853   0.04480   0.0518   0.0030   1.0000
  11.750   0.8097   0.05169   0.04813   0.0533   0.0030   1.0000
  12.000   0.7926   0.05545   0.05206   0.0540   0.0030   1.0000
  12.250   0.7716   0.06019   0.05698   0.0534   0.0030   1.0000
  12.500   0.7599   0.06413   0.06103   0.0521   0.0031   1.0000
  12.750   0.7385   0.07011   0.06717   0.0494   0.0031   1.0000
  13.000   0.7220   0.07585   0.07303   0.0462   0.0031   1.0000
  13.250   0.6970   0.08392   0.08125   0.0414   0.0032   1.0000
  13.500   0.6815   0.09082   0.08825   0.0372   0.0032   1.0000
  13.750   0.6622   0.09941   0.09694   0.0320   0.0033   1.0000
  14.000   0.6388   0.11015   0.10777   0.0260   0.0033   1.0000
  14.250   0.6216   0.11998   0.11764   0.0212   0.0034   1.0000
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