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GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 459 AIRFOIL (goe459-il)
Reynolds number: 200,000
Max Cl/Cd: 49.27 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe459-il-200000.txt
Download as CSV file: xf-goe459-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 459 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.9256   0.08235   0.07776  -0.0454   1.0000   0.0339
 -15.250  -0.9534   0.07480   0.07002  -0.0495   1.0000   0.0337
 -15.000  -0.9845   0.06778   0.06273  -0.0534   1.0000   0.0340
 -14.750  -1.0061   0.06240   0.05712  -0.0553   1.0000   0.0340
 -14.500  -1.0270   0.05768   0.05216  -0.0563   1.0000   0.0341
 -14.250  -1.0383   0.05376   0.04810  -0.0562   1.0000   0.0345
 -14.000  -1.0301   0.05245   0.04688  -0.0559   1.0000   0.0356
 -13.750  -1.0339   0.05018   0.04453  -0.0553   1.0000   0.0364
 -13.500  -1.0390   0.04793   0.04214  -0.0542   1.0000   0.0373
 -13.250  -1.0464   0.04544   0.03947  -0.0526   1.0000   0.0381
 -13.000  -1.0546   0.04311   0.03692  -0.0503   1.0000   0.0391
 -12.750  -1.0651   0.04117   0.03468  -0.0471   1.0000   0.0403
 -12.500  -1.0734   0.03919   0.03242  -0.0435   1.0000   0.0412
 -12.250  -1.0624   0.03779   0.03115  -0.0421   1.0000   0.0433
 -12.000  -1.0607   0.03689   0.03017  -0.0389   1.0000   0.0450
 -11.750  -1.0624   0.03581   0.02893  -0.0349   1.0000   0.0471
 -11.500  -1.0674   0.03502   0.02789  -0.0300   1.0000   0.0489
 -11.250  -1.0563   0.03296   0.02585  -0.0283   1.0000   0.0522
 -11.000  -1.0487   0.03211   0.02495  -0.0255   1.0000   0.0552
 -10.750  -1.0447   0.03143   0.02404  -0.0217   1.0000   0.0584
 -10.500  -1.0316   0.02957   0.02213  -0.0200   1.0000   0.0620
 -10.250  -1.0199   0.02889   0.02143  -0.0177   1.0000   0.0654
 -10.000  -1.0089   0.02821   0.02058  -0.0150   1.0000   0.0685
  -9.750  -0.9953   0.02700   0.01920  -0.0128   1.0000   0.0713
  -9.500  -0.9781   0.02591   0.01816  -0.0114   1.0000   0.0746
  -9.250  -0.9630   0.02522   0.01742  -0.0094   1.0000   0.0775
  -9.000  -0.9482   0.02461   0.01667  -0.0071   1.0000   0.0804
  -8.750  -0.9319   0.02375   0.01570  -0.0053   1.0000   0.0832
  -8.500  -0.9154   0.02286   0.01489  -0.0036   1.0000   0.0870
  -8.250  -0.8994   0.02230   0.01429  -0.0016   1.0000   0.0903
  -8.000  -0.8822   0.02166   0.01356   0.0004   1.0000   0.0927
  -7.750  -0.8649   0.02107   0.01285   0.0023   1.0000   0.0945
  -7.500  -0.8487   0.02008   0.01193   0.0043   1.0000   0.0971
  -7.250  -0.8337   0.01942   0.01129   0.0066   1.0000   0.0995
  -7.000  -0.8189   0.01887   0.01074   0.0089   1.0000   0.1021
  -6.750  -0.8042   0.01837   0.01019   0.0113   1.0000   0.1051
  -6.500  -0.7898   0.01788   0.00966   0.0138   1.0000   0.1084
  -6.250  -0.7778   0.01730   0.00915   0.0166   1.0000   0.1130
  -6.000  -0.7637   0.01690   0.00874   0.0191   1.0000   0.1194
  -5.750  -0.7515   0.01638   0.00831   0.0219   1.0000   0.1284
  -5.500  -0.7392   0.01587   0.00789   0.0246   1.0000   0.1438
  -5.250  -0.7287   0.01523   0.00745   0.0276   1.0000   0.1748
  -5.000  -0.7176   0.01469   0.00714   0.0304   1.0000   0.2155
  -4.750  -0.7046   0.01432   0.00693   0.0328   1.0000   0.2529
  -4.500  -0.6909   0.01402   0.00674   0.0352   1.0000   0.2845
  -4.250  -0.6553   0.01372   0.00664   0.0330   0.9949   0.3288
  -4.000  -0.6212   0.01334   0.00654   0.0312   0.9887   0.3816
  -3.750  -0.5845   0.01308   0.00656   0.0290   0.9830   0.4465
  -3.500  -0.5533   0.01281   0.00649   0.0281   0.9753   0.5011
  -3.250  -0.5153   0.01264   0.00650   0.0259   0.9704   0.5499
  -3.000  -0.4859   0.01242   0.00643   0.0257   0.9617   0.5912
  -2.750  -0.4466   0.01227   0.00644   0.0235   0.9569   0.6322
  -2.500  -0.4175   0.01212   0.00637   0.0234   0.9479   0.6631
  -2.250  -0.3780   0.01198   0.00633   0.0212   0.9432   0.6951
  -2.000  -0.3477   0.01185   0.00628   0.0210   0.9345   0.7233
  -1.750  -0.3079   0.01169   0.00619   0.0190   0.9294   0.7512
  -1.500  -0.2700   0.01157   0.00616   0.0173   0.9236   0.7741
  -1.250  -0.2323   0.01144   0.00607   0.0157   0.9167   0.7948
  -1.000  -0.1835   0.01125   0.00594   0.0120   0.9131   0.8167
  -0.750  -0.1413   0.01116   0.00590   0.0098   0.9049   0.8368
  -0.500  -0.0913   0.01102   0.00579   0.0060   0.8984   0.8539
  -0.250  -0.0471   0.01094   0.00572   0.0034   0.8883   0.8679
   0.000   0.0000   0.01084   0.00560   0.0000   0.8799   0.8799
   0.250   0.0473   0.01094   0.00572  -0.0034   0.8678   0.8883
   0.500   0.0913   0.01102   0.00579  -0.0060   0.8540   0.8984
   0.750   0.1414   0.01116   0.00590  -0.0098   0.8368   0.9050
   1.000   0.1839   0.01126   0.00594  -0.0121   0.8166   0.9132
   1.250   0.2325   0.01144   0.00607  -0.0158   0.7951   0.9167
   1.500   0.2701   0.01157   0.00616  -0.0173   0.7742   0.9236
   1.750   0.3079   0.01169   0.00619  -0.0190   0.7512   0.9294
   2.000   0.3478   0.01185   0.00628  -0.0211   0.7237   0.9345
   2.250   0.3780   0.01198   0.00632  -0.0212   0.6942   0.9432
   2.500   0.4175   0.01212   0.00637  -0.0233   0.6621   0.9480
   2.750   0.4466   0.01227   0.00643  -0.0235   0.6318   0.9569
   3.000   0.4857   0.01242   0.00642  -0.0256   0.5898   0.9617
   3.250   0.5152   0.01263   0.00650  -0.0259   0.5496   0.9704
   3.500   0.5534   0.01281   0.00649  -0.0281   0.5009   0.9754
   3.750   0.5846   0.01308   0.00655  -0.0290   0.4463   0.9831
   4.000   0.6211   0.01334   0.00654  -0.0312   0.3817   0.9887
   4.250   0.6554   0.01371   0.00664  -0.0330   0.3289   0.9949
   4.500   0.6908   0.01402   0.00674  -0.0352   0.2848   1.0000
   4.750   0.7045   0.01432   0.00693  -0.0328   0.2524   1.0000
   5.000   0.7175   0.01468   0.00713  -0.0304   0.2153   1.0000
   5.250   0.7287   0.01522   0.00744  -0.0276   0.1759   1.0000
   5.500   0.7392   0.01587   0.00788  -0.0246   0.1441   1.0000
   5.750   0.7513   0.01639   0.00832  -0.0219   0.1280   1.0000
   6.000   0.7637   0.01690   0.00874  -0.0191   0.1197   1.0000
   6.250   0.7778   0.01729   0.00915  -0.0166   0.1131   1.0000
   6.500   0.7897   0.01789   0.00966  -0.0138   0.1084   1.0000
   6.750   0.8041   0.01837   0.01019  -0.0113   0.1053   1.0000
   7.000   0.8189   0.01887   0.01073  -0.0089   0.1022   1.0000
   7.250   0.8338   0.01942   0.01129  -0.0066   0.0997   1.0000
   7.500   0.8487   0.02007   0.01192  -0.0043   0.0972   1.0000
   7.750   0.8649   0.02107   0.01285  -0.0023   0.0945   1.0000
   8.000   0.8822   0.02165   0.01355  -0.0004   0.0927   1.0000
   8.250   0.8994   0.02229   0.01428   0.0016   0.0904   1.0000
   8.500   0.9154   0.02286   0.01489   0.0036   0.0870   1.0000
   8.750   0.9319   0.02372   0.01567   0.0053   0.0833   1.0000
   9.000   0.9481   0.02459   0.01665   0.0072   0.0803   1.0000
   9.250   0.9631   0.02522   0.01742   0.0093   0.0776   1.0000
   9.500   0.9780   0.02588   0.01814   0.0114   0.0745   1.0000
   9.750   0.9954   0.02704   0.01923   0.0128   0.0712   1.0000
  10.000   1.0086   0.02818   0.02055   0.0150   0.0684   1.0000
  10.250   1.0199   0.02889   0.02143   0.0177   0.0653   1.0000
  10.500   1.0319   0.02963   0.02220   0.0200   0.0620   1.0000
  10.750   1.0443   0.03140   0.02401   0.0218   0.0583   1.0000
  11.000   1.0489   0.03215   0.02499   0.0254   0.0552   1.0000
  11.250   1.0566   0.03297   0.02587   0.0283   0.0521   1.0000
  11.500   1.0687   0.03512   0.02797   0.0297   0.0490   1.0000
  11.750   1.0623   0.03583   0.02896   0.0349   0.0470   1.0000
  12.000   1.0605   0.03676   0.03004   0.0390   0.0448   1.0000
  12.250   1.0630   0.03768   0.03102   0.0420   0.0431   1.0000
  12.500   1.0736   0.03914   0.03238   0.0435   0.0413   1.0000
  12.750   1.0645   0.04109   0.03461   0.0472   0.0402   1.0000
  13.000   1.0557   0.04318   0.03698   0.0502   0.0392   1.0000
  13.250   1.0470   0.04555   0.03959   0.0525   0.0383   1.0000
  13.500   1.0409   0.04775   0.04195   0.0541   0.0371   1.0000
  13.750   1.0329   0.05046   0.04483   0.0552   0.0365   1.0000
  14.000   1.0296   0.05263   0.04709   0.0557   0.0358   1.0000
  14.250   1.0297   0.05476   0.04924   0.0560   0.0350   1.0000
  14.500   1.0273   0.05774   0.05221   0.0561   0.0341   1.0000
  14.750   1.0081   0.06235   0.05707   0.0552   0.0340   1.0000
  15.000   0.9845   0.06777   0.06273   0.0530   0.0338   1.0000
  15.250   0.9585   0.07434   0.06953   0.0499   0.0339   1.0000
  15.500   0.9316   0.08162   0.07700   0.0458   0.0339   1.0000
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