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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 500,000
Max Cl/Cd: 101.65 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe173-il-500000.txt
Download as CSV file: xf-goe173-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 173 (ALBATROS 6020) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2693   0.09407   0.09201  -0.0242   1.0000   0.0146
  -7.500  -0.2720   0.09215   0.09014  -0.0231   1.0000   0.0150
  -7.250  -0.2805   0.09080   0.08885  -0.0209   1.0000   0.0153
  -7.000  -0.2524   0.08639   0.08444  -0.0310   0.9953   0.0156
  -6.750  -0.2176   0.08128   0.07931  -0.0428   0.9890   0.0157
  -6.500  -0.1800   0.07589   0.07389  -0.0535   0.9840   0.0157
  -6.250  -0.1468   0.07093   0.06890  -0.0616   0.9749   0.0158
  -6.000  -0.1313   0.06618   0.06416  -0.0627   0.9656   0.0162
  -5.750  -0.1036   0.06250   0.06045  -0.0673   0.9494   0.0166
  -5.500  -0.0683   0.05843   0.05629  -0.0743   0.9267   0.0174
  -5.250  -0.0323   0.05428   0.05199  -0.0813   0.8920   0.0188
  -5.000   0.0178   0.04961   0.04699  -0.0917   0.8571   0.0204
  -4.750   0.0508   0.04588   0.04299  -0.0961   0.8308   0.0205
  -4.500   0.0733   0.04063   0.03755  -0.0995   0.8117   0.0210
  -4.250   0.0951   0.03826   0.03505  -0.1006   0.7948   0.0215
  -4.000   0.1205   0.03596   0.03260  -0.1021   0.7801   0.0221
  -3.750   0.1490   0.03345   0.02990  -0.1040   0.7670   0.0234
  -3.500   0.1892   0.03066   0.02674  -0.1062   0.7552   0.0268
  -3.250   0.2211   0.02776   0.02348  -0.1074   0.7435   0.0271
  -3.000   0.2464   0.02333   0.01883  -0.1094   0.7324   0.0286
  -2.750   0.2727   0.02206   0.01743  -0.1098   0.7207   0.0301
  -2.500   0.3023   0.02049   0.01556  -0.1100   0.7106   0.0339
  -2.250   0.3332   0.01781   0.01239  -0.1106   0.7011   0.0376
  -2.000   0.3598   0.01695   0.01148  -0.1108   0.6908   0.0403
  -1.750   0.3889   0.01792   0.01218  -0.1101   0.6802   0.0472
  -1.500   0.4157   0.01513   0.00925  -0.1110   0.6702   0.0533
  -1.250   0.4437   0.01442   0.00835  -0.1111   0.6601   0.0641
  -1.000   0.4713   0.01398   0.00775  -0.1111   0.6501   0.0770
  -0.750   0.5029   0.01235   0.00563  -0.1101   0.6406   0.0478
  -0.500   0.5310   0.01115   0.00432  -0.1099   0.6302   0.0439
  -0.250   0.5587   0.01066   0.00373  -0.1097   0.6194   0.0436
   0.000   0.5862   0.01032   0.00330  -0.1095   0.6078   0.0441
   0.500   0.6411   0.00978   0.00261  -0.1091   0.5820   0.0444
   0.750   0.6685   0.00964   0.00241  -0.1089   0.5682   0.0451
   1.000   0.6959   0.00956   0.00227  -0.1087   0.5538   0.0459
   1.250   0.7230   0.00955   0.00218  -0.1085   0.5381   0.0470
   1.500   0.7501   0.00955   0.00210  -0.1083   0.5206   0.0491
   1.750   0.7771   0.00960   0.00206  -0.1081   0.5001   0.0524
   2.000   0.8036   0.00970   0.00209  -0.1078   0.4755   0.0661
   2.250   0.8237   0.00811   0.00236  -0.1066   0.4472   1.0000
   2.500   0.8491   0.00844   0.00246  -0.1062   0.4108   1.0000
   2.750   0.8743   0.00881   0.00260  -0.1058   0.3806   1.0000
   3.000   0.8999   0.00913   0.00277  -0.1054   0.3609   1.0000
   3.250   0.9258   0.00943   0.00295  -0.1051   0.3470   1.0000
   3.750   0.9779   0.00995   0.00334  -0.1046   0.3278   1.0000
   4.000   1.0036   0.01025   0.00356  -0.1042   0.3207   1.0000
   4.250   1.0301   0.01044   0.00375  -0.1040   0.3148   1.0000
   4.500   1.0559   0.01071   0.00400  -0.1037   0.3094   1.0000
   4.750   1.0818   0.01098   0.00425  -0.1035   0.3048   1.0000
   5.000   1.1081   0.01118   0.00447  -0.1032   0.3004   1.0000
   5.250   1.1336   0.01145   0.00471  -0.1029   0.2947   1.0000
   5.500   1.1595   0.01168   0.00496  -0.1027   0.2887   1.0000
   5.750   1.1855   0.01187   0.00517  -0.1025   0.2825   1.0000
   6.000   1.2105   0.01217   0.00544  -0.1021   0.2768   1.0000
   6.250   1.2370   0.01230   0.00563  -0.1019   0.2703   1.0000
   6.500   1.2623   0.01253   0.00585  -0.1016   0.2610   1.0000
   6.750   1.2878   0.01272   0.00604  -0.1014   0.2514   1.0000
   7.000   1.3133   0.01292   0.00624  -0.1011   0.2389   1.0000
   7.250   1.3377   0.01323   0.00646  -0.1007   0.2179   1.0000
   7.500   1.3555   0.01422   0.00701  -0.0995   0.1459   1.0000
   7.750   1.3566   0.01702   0.00902  -0.0959   0.0270   1.0000
   8.000   1.3758   0.01784   0.00985  -0.0946   0.0188   1.0000
   8.250   1.3954   0.01857   0.01068  -0.0933   0.0166   1.0000
   8.500   1.4130   0.01948   0.01175  -0.0918   0.0146   1.0000
   8.750   1.4313   0.02024   0.01261  -0.0904   0.0140   1.0000
   9.000   1.4474   0.02115   0.01364  -0.0887   0.0134   1.0000
   9.250   1.4613   0.02217   0.01477  -0.0868   0.0128   1.0000
   9.500   1.4725   0.02329   0.01601  -0.0845   0.0123   1.0000
   9.750   1.4787   0.02450   0.01733  -0.0813   0.0119   1.0000
  10.000   1.4817   0.02589   0.01883  -0.0780   0.0116   1.0000
  10.250   1.4823   0.02750   0.02055  -0.0747   0.0113   1.0000
  10.500   1.4795   0.02949   0.02267  -0.0716   0.0109   1.0000
  10.750   1.4722   0.03207   0.02537  -0.0687   0.0106   1.0000
  11.000   1.4616   0.03533   0.02876  -0.0664   0.0103   1.0000
  11.250   1.4492   0.03909   0.03264  -0.0645   0.0101   1.0000
  11.500   1.4502   0.04168   0.03534  -0.0636   0.0099   1.0000
  11.750   1.4528   0.04416   0.03793  -0.0629   0.0098   1.0000
  12.000   1.4544   0.04682   0.04069  -0.0622   0.0097   1.0000
  12.250   1.4548   0.04962   0.04359  -0.0615   0.0095   1.0000
  12.500   1.4549   0.05247   0.04655  -0.0607   0.0094   1.0000
  12.750   1.4550   0.05535   0.04953  -0.0600   0.0093   1.0000
  13.000   1.4551   0.05822   0.05251  -0.0592   0.0092   1.0000
  13.250   1.4553   0.06112   0.05553  -0.0584   0.0091   1.0000
  13.500   1.4557   0.06402   0.05854  -0.0576   0.0091   1.0000
  13.750   1.4560   0.06698   0.06163  -0.0567   0.0090   1.0000
  14.000   1.4561   0.07003   0.06481  -0.0557   0.0091   1.0000
  14.250   1.4558   0.07326   0.06818  -0.0547   0.0092   1.0000
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