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GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 15 AIRFOIL (goe15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.66 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe15-il-1000000.txt
Download as CSV file: xf-goe15-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 15 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.0313   0.09036   0.08836  -0.0916   0.9026   0.0185
  -9.250   0.0525   0.08730   0.08513  -0.0960   0.8691   0.0194
  -9.000   0.0577   0.08504   0.08268  -0.0973   0.8271   0.0199
  -8.750   0.0598   0.08330   0.08075  -0.0972   0.7862   0.0199
  -8.500   0.0614   0.08143   0.07877  -0.0974   0.7625   0.0199
  -8.250   0.0694   0.07863   0.07590  -0.0969   0.7492   0.0201
  -8.000   0.0767   0.07668   0.07392  -0.0969   0.7393   0.0202
  -7.750   0.0833   0.07493   0.07213  -0.0967   0.7306   0.0203
  -7.500   0.0888   0.07324   0.07043  -0.0965   0.7235   0.0205
  -7.250   0.0919   0.07172   0.06889  -0.0960   0.7165   0.0207
  -7.000   0.0995   0.06997   0.06714  -0.0965   0.7107   0.0213
  -6.750   0.1091   0.06794   0.06509  -0.0975   0.7052   0.0219
  -6.500   0.1197   0.06570   0.06282  -0.0991   0.6998   0.0227
  -6.250   0.1331   0.06339   0.06048  -0.1022   0.6949   0.0230
  -6.000   0.1488   0.06095   0.05800  -0.1053   0.6901   0.0230
  -5.750   0.1601   0.05810   0.05514  -0.1051   0.6849   0.0232
  -5.500   0.1742   0.05609   0.05308  -0.1054   0.6790   0.0233
  -5.250   0.1910   0.05422   0.05121  -0.1063   0.6740   0.0236
  -5.000   0.2092   0.05234   0.04930  -0.1074   0.6678   0.0239
  -4.750   0.2280   0.05046   0.04735  -0.1085   0.6618   0.0243
  -4.500   0.2486   0.04844   0.04531  -0.1099   0.6562   0.0250
  -4.250   0.2738   0.04626   0.04306  -0.1120   0.6494   0.0261
  -4.000   0.3041   0.04406   0.04070  -0.1150   0.6425   0.0263
  -3.750   0.3238   0.04137   0.03796  -0.1157   0.6345   0.0264
  -3.500   0.3413   0.03946   0.03600  -0.1156   0.6248   0.0266
  -3.250   0.3622   0.03786   0.03435  -0.1158   0.6126   0.0268
  -3.000   0.3841   0.03640   0.03279  -0.1161   0.5974   0.0271
  -2.750   0.4066   0.03501   0.03128  -0.1163   0.5787   0.0275
  -2.500   0.4292   0.03364   0.02976  -0.1163   0.5556   0.0282
  -2.250   0.4530   0.03229   0.02821  -0.1163   0.5274   0.0293
  -2.000   0.4866   0.03096   0.02656  -0.1166   0.5020   0.0298
  -1.750   0.5057   0.02898   0.02443  -0.1161   0.4813   0.0299
  -1.500   0.5252   0.02771   0.02306  -0.1156   0.4656   0.0301
  -1.250   0.5473   0.02667   0.02192  -0.1152   0.4543   0.0304
  -1.000   0.5709   0.02571   0.02087  -0.1149   0.4458   0.0309
  -0.750   0.5951   0.02475   0.01980  -0.1145   0.4384   0.0314
  -0.500   0.6208   0.02373   0.01869  -0.1141   0.4329   0.0326
  -0.250   0.6531   0.02289   0.01759  -0.1132   0.4275   0.0335
   0.000   0.6746   0.02124   0.01583  -0.1126   0.4217   0.0338
   0.250   0.6980   0.02032   0.01489  -0.1123   0.4183   0.0340
   0.500   0.7221   0.01960   0.01411  -0.1119   0.4145   0.0344
   0.750   0.7467   0.01897   0.01340  -0.1113   0.4105   0.0352
   1.000   0.7754   0.01860   0.01283  -0.1102   0.4061   0.0374
   1.250   0.8016   0.01788   0.01198  -0.1094   0.4029   0.0375
   1.500   0.8249   0.01656   0.01061  -0.1089   0.4002   0.0380
   1.750   0.8492   0.01604   0.01006  -0.1085   0.3970   0.0384
   2.000   0.8738   0.01560   0.00957  -0.1079   0.3935   0.0391
   2.250   0.8982   0.01525   0.00911  -0.1071   0.3886   0.0407
   2.500   0.9264   0.01508   0.00874  -0.1060   0.3854   0.0420
   2.750   0.9503   0.01405   0.00769  -0.1055   0.3826   0.0427
   3.000   0.9751   0.01373   0.00735  -0.1050   0.3793   0.0432
   3.250   0.9998   0.01351   0.00709  -0.1044   0.3758   0.0446
   3.500   1.0255   0.01365   0.00705  -0.1033   0.3710   0.0471
   3.750   1.0496   0.01282   0.00621  -0.1028   0.3680   0.0480
   4.000   1.0748   0.01259   0.00599  -0.1023   0.3652   0.0488
   4.250   1.0998   0.01243   0.00581  -0.1018   0.3623   0.0504
   4.500   1.1246   0.01223   0.00552  -0.1010   0.3592   0.0538
   4.750   1.1482   0.01210   0.00540  -0.1002   0.3559   0.0549
   5.000   1.1717   0.01207   0.00534  -0.0994   0.3525   0.0570
   5.250   1.1969   0.01191   0.00518  -0.0989   0.3502   0.0611
   5.500   1.2212   0.01180   0.00511  -0.0983   0.3470   0.0630
   5.750   1.2450   0.01179   0.00508  -0.0975   0.3434   0.0690
   6.000   1.2675   0.01177   0.00508  -0.0966   0.3397   0.0723
   6.250   1.2893   0.01176   0.00506  -0.0954   0.3361   0.0726
   6.500   1.3114   0.01147   0.00474  -0.0940   0.3337   0.0555
   6.750   1.3346   0.01150   0.00481  -0.0932   0.3304   0.0570
   7.000   1.3568   0.01157   0.00489  -0.0922   0.3267   0.0582
   7.250   1.3778   0.01170   0.00500  -0.0910   0.3226   0.0590
   7.500   1.3986   0.01180   0.00512  -0.0898   0.3189   0.0599
   7.750   1.4197   0.01183   0.00519  -0.0885   0.3152   0.0616
   8.000   1.4389   0.01196   0.00532  -0.0870   0.3093   0.0643
   8.250   1.4571   0.01214   0.00549  -0.0853   0.3028   0.0662
   8.500   1.4771   0.01228   0.00565  -0.0839   0.2969   0.0683
   8.750   1.4945   0.01252   0.00587  -0.0821   0.2903   0.0726
   9.000   1.5136   0.01272   0.00609  -0.0807   0.2836   0.0789
   9.250   1.5761   0.01225   0.00684  -0.0894   0.2697   1.0000
   9.500   1.5915   0.01261   0.00715  -0.0874   0.2594   1.0000
   9.750   1.6068   0.01299   0.00749  -0.0854   0.2475   1.0000
  10.000   1.6207   0.01347   0.00790  -0.0832   0.2346   1.0000
  10.250   1.6339   0.01399   0.00837  -0.0811   0.2223   1.0000
  10.500   1.6458   0.01459   0.00891  -0.0788   0.2094   1.0000
  10.750   1.6569   0.01527   0.00951  -0.0765   0.1969   1.0000
  11.000   1.6679   0.01597   0.01017  -0.0742   0.1856   1.0000
  11.250   1.6789   0.01670   0.01086  -0.0721   0.1752   1.0000
  11.500   1.6896   0.01747   0.01160  -0.0701   0.1668   1.0000
  11.750   1.7024   0.01815   0.01229  -0.0684   0.1611   1.0000
  12.000   1.7121   0.01905   0.01317  -0.0664   0.1536   1.0000
  12.250   1.7239   0.01984   0.01398  -0.0648   0.1473   1.0000
  12.500   1.7319   0.02092   0.01502  -0.0629   0.1391   1.0000
  12.750   1.7376   0.02218   0.01624  -0.0609   0.1284   1.0000
  13.000   1.7396   0.02377   0.01777  -0.0587   0.1145   1.0000
  13.250   1.7318   0.02618   0.02005  -0.0560   0.0934   1.0000
  13.500   1.7187   0.02923   0.02300  -0.0534   0.0737   1.0000
  13.750   1.7013   0.03290   0.02658  -0.0511   0.0553   1.0000
  14.000   1.6787   0.03730   0.03090  -0.0490   0.0370   1.0000
  14.250   1.6585   0.04171   0.03529  -0.0475   0.0223   1.0000
  14.500   1.6479   0.04535   0.03898  -0.0466   0.0179   1.0000
  14.750   1.6427   0.04854   0.04224  -0.0460   0.0166   1.0000
  15.000   1.6382   0.05176   0.04554  -0.0455   0.0157   1.0000
  15.250   1.6349   0.05494   0.04881  -0.0453   0.0151   1.0000
  15.500   1.6295   0.05842   0.05239  -0.0451   0.0147   1.0000
  15.750   1.6231   0.06216   0.05622  -0.0452   0.0143   1.0000
  16.000   1.6155   0.06615   0.06030  -0.0453   0.0140   1.0000
  16.250   1.6064   0.07036   0.06462  -0.0456   0.0136   1.0000
  16.500   1.5951   0.07498   0.06933  -0.0461   0.0132   1.0000
  16.750   1.5827   0.07983   0.07429  -0.0467   0.0129   1.0000
  17.000   1.5750   0.08401   0.07857  -0.0472   0.0127   1.0000
  17.250   1.5663   0.08836   0.08301  -0.0479   0.0126   1.0000
  17.500   1.5571   0.09279   0.08753  -0.0486   0.0125   1.0000
  17.750   1.5491   0.09709   0.09192  -0.0493   0.0122   1.0000
  18.000   1.5388   0.10174   0.09666  -0.0502   0.0121   1.0000
  18.250   1.5297   0.10621   0.10122  -0.0511   0.0118   1.0000
  18.500   1.5199   0.11085   0.10594  -0.0522   0.0116   1.0000
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