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GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 550 AIRFOIL (goe550-il)
Reynolds number: 500,000
Max Cl/Cd: 98.38 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe550-il-500000-n5.txt
Download as CSV file: xf-goe550-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 550 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.6592   0.13433   0.13146  -0.0379   1.0000   0.0209
 -17.250  -0.6859   0.12513   0.12216  -0.0425   1.0000   0.0216
 -17.000  -0.6943   0.11985   0.11686  -0.0451   1.0000   0.0222
 -16.750  -0.7097   0.11332   0.11029  -0.0485   1.0000   0.0227
 -16.500  -0.7258   0.10685   0.10376  -0.0518   1.0000   0.0233
 -16.250  -0.7409   0.10071   0.09756  -0.0549   1.0000   0.0238
 -16.000  -0.7559   0.09476   0.09154  -0.0579   1.0000   0.0242
 -15.750  -0.7707   0.08900   0.08570  -0.0609   1.0000   0.0247
 -15.500  -0.7825   0.08394   0.08056  -0.0634   1.0000   0.0251
 -15.250  -0.7958   0.07874   0.07528  -0.0660   1.0000   0.0256
 -15.000  -0.8106   0.07359   0.07009  -0.0686   1.0000   0.0259
 -14.750  -0.8276   0.06842   0.06488  -0.0712   1.0000   0.0262
 -14.500  -0.8505   0.06295   0.05936  -0.0739   1.0000   0.0263
 -14.250  -0.8787   0.05721   0.05357  -0.0765   1.0000   0.0264
 -14.000  -0.9164   0.05106   0.04736  -0.0789   1.0000   0.0262
 -13.750  -0.9931   0.04327   0.03951  -0.0794   1.0000   0.0254
 -13.500  -1.0218   0.03062   0.02648  -0.0936   0.9974   0.0254
 -13.250  -0.9985   0.02770   0.02338  -0.0982   0.9943   0.0263
 -13.000  -0.9747   0.02584   0.02142  -0.1007   0.9913   0.0274
 -12.750  -0.9485   0.02450   0.01996  -0.1026   0.9882   0.0286
 -12.500  -0.9199   0.02341   0.01874  -0.1044   0.9856   0.0298
 -12.250  -0.8902   0.02231   0.01752  -0.1064   0.9836   0.0308
 -12.000  -0.8663   0.02127   0.01641  -0.1070   0.9793   0.0320
 -11.750  -0.8381   0.02043   0.01550  -0.1082   0.9759   0.0332
 -11.500  -0.8076   0.01970   0.01466  -0.1096   0.9735   0.0345
 -11.250  -0.7766   0.01901   0.01387  -0.1109   0.9712   0.0356
 -11.000  -0.7531   0.01828   0.01307  -0.1108   0.9651   0.0367
 -10.750  -0.7235   0.01755   0.01229  -0.1119   0.9617   0.0381
 -10.500  -0.6916   0.01693   0.01160  -0.1132   0.9593   0.0396
 -10.250  -0.6670   0.01643   0.01103  -0.1129   0.9524   0.0409
 -10.000  -0.6358   0.01596   0.01046  -0.1139   0.9480   0.0422
  -9.750  -0.6018   0.01526   0.00972  -0.1157   0.9449   0.0441
  -9.500  -0.5743   0.01474   0.00915  -0.1159   0.9370   0.0458
  -9.250  -0.5397   0.01425   0.00858  -0.1176   0.9315   0.0476
  -9.000  -0.5068   0.01382   0.00807  -0.1187   0.9232   0.0491
  -8.750  -0.4712   0.01331   0.00747  -0.1206   0.9148   0.0511
  -8.500  -0.4393   0.01284   0.00695  -0.1216   0.9038   0.0535
  -8.250  -0.4072   0.01246   0.00648  -0.1226   0.8930   0.0560
  -7.750  -0.3480   0.01181   0.00567  -0.1234   0.8694   0.0614
  -7.500  -0.3201   0.01153   0.00532  -0.1234   0.8578   0.0655
  -7.250  -0.2926   0.01127   0.00500  -0.1233   0.8468   0.0703
  -7.000  -0.2657   0.01104   0.00472  -0.1231   0.8361   0.0763
  -6.750  -0.2388   0.01083   0.00447  -0.1229   0.8264   0.0823
  -6.500  -0.2118   0.01067   0.00425  -0.1226   0.8167   0.0886
  -6.250  -0.1851   0.01049   0.00402  -0.1223   0.8078   0.0938
  -6.000  -0.1581   0.01035   0.00382  -0.1220   0.7995   0.0997
  -5.750  -0.1311   0.01023   0.00364  -0.1217   0.7912   0.1041
  -5.500  -0.1044   0.01006   0.00343  -0.1214   0.7829   0.1098
  -5.250  -0.0774   0.00993   0.00327  -0.1211   0.7750   0.1148
  -5.000  -0.0504   0.00980   0.00310  -0.1208   0.7674   0.1201
  -4.750  -0.0234   0.00966   0.00295  -0.1205   0.7600   0.1268
  -4.500   0.0035   0.00956   0.00281  -0.1202   0.7519   0.1335
  -4.250   0.0305   0.00944   0.00269  -0.1199   0.7446   0.1429
  -4.000   0.0576   0.00934   0.00260  -0.1196   0.7369   0.1529
  -3.750   0.0847   0.00928   0.00252  -0.1193   0.7296   0.1630
  -3.500   0.1121   0.00923   0.00246  -0.1191   0.7214   0.1744
  -3.250   0.1391   0.00920   0.00242  -0.1187   0.7132   0.1842
  -3.000   0.1662   0.00918   0.00236  -0.1184   0.7031   0.1908
  -2.750   0.1928   0.00917   0.00231  -0.1179   0.6912   0.1964
  -2.500   0.2193   0.00918   0.00226  -0.1174   0.6785   0.2016
  -2.250   0.2459   0.00920   0.00220  -0.1170   0.6665   0.2059
  -2.000   0.2729   0.00917   0.00217  -0.1166   0.6565   0.2103
  -1.750   0.2997   0.00918   0.00214  -0.1162   0.6471   0.2143
  -1.500   0.3267   0.00919   0.00210  -0.1159   0.6373   0.2181
  -1.250   0.3535   0.00922   0.00207  -0.1155   0.6273   0.2210
  -1.000   0.3800   0.00922   0.00205  -0.1150   0.6168   0.2245
  -0.750   0.4069   0.00923   0.00205  -0.1147   0.6072   0.2281
  -0.500   0.4334   0.00927   0.00204  -0.1142   0.5976   0.2317
  -0.250   0.4601   0.00931   0.00205  -0.1138   0.5870   0.2358
   0.000   0.4865   0.00935   0.00206  -0.1134   0.5770   0.2401
   0.500   0.5395   0.00943   0.00212  -0.1125   0.5582   0.2497
   0.750   0.5656   0.00950   0.00215  -0.1120   0.5493   0.2534
   1.000   0.5921   0.00954   0.00219  -0.1116   0.5397   0.2580
   1.250   0.6181   0.00960   0.00225  -0.1111   0.5304   0.2628
   1.500   0.6443   0.00967   0.00230  -0.1107   0.5209   0.2671
   1.750   0.6706   0.00974   0.00236  -0.1102   0.5127   0.2710
   2.000   0.6962   0.00981   0.00243  -0.1096   0.5024   0.2762
   2.250   0.7221   0.00988   0.00250  -0.1091   0.4918   0.2820
   2.500   0.7473   0.01000   0.00259  -0.1085   0.4797   0.2873
   2.750   0.7724   0.01009   0.00268  -0.1078   0.4682   0.2934
   3.000   0.7981   0.01017   0.00277  -0.1073   0.4575   0.3005
   3.250   0.8232   0.01028   0.00288  -0.1067   0.4471   0.3081
   3.500   0.8480   0.01039   0.00299  -0.1060   0.4360   0.3177
   3.750   0.8725   0.01050   0.00312  -0.1053   0.4225   0.3302
   4.000   0.8963   0.01063   0.00327  -0.1044   0.4077   0.3498
   4.250   0.9196   0.01072   0.00346  -0.1036   0.3934   0.3971
   4.500   0.9426   0.01079   0.00367  -0.1026   0.3809   0.4689
   4.750   0.9655   0.01089   0.00386  -0.1017   0.3703   0.5174
   5.000   0.9853   0.01063   0.00411  -0.1001   0.3616   0.7128
   5.500   1.0468   0.01064   0.00457  -0.1013   0.3437   1.0000
   5.750   1.0696   0.01088   0.00478  -0.1003   0.3351   1.0000
   6.000   1.0926   0.01111   0.00500  -0.0993   0.3268   1.0000
   6.250   1.1153   0.01135   0.00523  -0.0983   0.3204   1.0000
   6.500   1.1377   0.01160   0.00546  -0.0972   0.3114   1.0000
   6.750   1.1588   0.01190   0.00571  -0.0959   0.2988   1.0000
   7.000   1.1787   0.01224   0.00599  -0.0945   0.2838   1.0000
   7.250   1.1988   0.01256   0.00628  -0.0930   0.2713   1.0000
   7.500   1.2174   0.01290   0.00656  -0.0913   0.2586   1.0000
   7.750   1.2358   0.01322   0.00686  -0.0896   0.2451   1.0000
   8.000   1.2520   0.01364   0.00721  -0.0875   0.2280   1.0000
   8.250   1.2646   0.01422   0.00766  -0.0848   0.2002   1.0000
   8.500   1.2692   0.01522   0.00837  -0.0811   0.1556   1.0000
   8.750   1.2767   0.01610   0.00910  -0.0778   0.1299   1.0000
   9.000   1.2886   0.01679   0.00972  -0.0753   0.1172   1.0000
   9.250   1.3023   0.01738   0.01030  -0.0732   0.1091   1.0000
   9.500   1.3158   0.01799   0.01091  -0.0711   0.1021   1.0000
   9.750   1.3300   0.01858   0.01151  -0.0691   0.0958   1.0000
  10.000   1.3425   0.01927   0.01218  -0.0670   0.0875   1.0000
  10.250   1.3540   0.02003   0.01292  -0.0648   0.0767   1.0000
  10.500   1.3639   0.02091   0.01376  -0.0626   0.0668   1.0000
  10.750   1.3728   0.02188   0.01469  -0.0604   0.0582   1.0000
  11.000   1.3819   0.02288   0.01568  -0.0583   0.0522   1.0000
  11.250   1.3905   0.02395   0.01675  -0.0563   0.0471   1.0000
  11.500   1.3999   0.02501   0.01785  -0.0544   0.0433   1.0000
  11.750   1.4073   0.02625   0.01911  -0.0526   0.0393   1.0000
  12.000   1.4159   0.02746   0.02035  -0.0510   0.0363   1.0000
  12.250   1.4228   0.02884   0.02176  -0.0493   0.0334   1.0000
  12.500   1.4303   0.03024   0.02320  -0.0479   0.0312   1.0000
  12.750   1.4368   0.03176   0.02476  -0.0465   0.0288   1.0000
  13.000   1.4419   0.03346   0.02650  -0.0451   0.0268   1.0000
  13.250   1.4481   0.03511   0.02822  -0.0440   0.0249   1.0000
  13.500   1.4522   0.03700   0.03016  -0.0428   0.0233   1.0000
  13.750   1.4561   0.03899   0.03221  -0.0418   0.0218   1.0000
  14.000   1.4599   0.04105   0.03432  -0.0410   0.0204   1.0000
  14.250   1.4624   0.04330   0.03664  -0.0402   0.0193   1.0000
  14.500   1.4635   0.04578   0.03917  -0.0396   0.0185   1.0000
  14.750   1.4659   0.04820   0.04168  -0.0391   0.0178   1.0000
  15.000   1.4673   0.05080   0.04437  -0.0388   0.0171   1.0000
  15.250   1.4675   0.05362   0.04726  -0.0386   0.0164   1.0000
  15.500   1.4666   0.05666   0.05037  -0.0385   0.0157   1.0000
  15.750   1.4647   0.05992   0.05371  -0.0386   0.0153   1.0000
  16.000   1.4626   0.06327   0.05715  -0.0388   0.0148   1.0000
  16.250   1.4612   0.06662   0.06061  -0.0392   0.0144   1.0000
  16.500   1.4593   0.07012   0.06420  -0.0397   0.0140   1.0000
  16.750   1.4567   0.07378   0.06796  -0.0403   0.0137   1.0000
  17.000   1.4532   0.07763   0.07189  -0.0411   0.0133   1.0000
  17.250   1.4486   0.08171   0.07607  -0.0421   0.0130   1.0000
  17.500   1.4437   0.08593   0.08039  -0.0432   0.0127   1.0000
  17.750   1.4373   0.09048   0.08502  -0.0445   0.0124   1.0000
  18.000   1.4304   0.09515   0.08979  -0.0460   0.0122   1.0000
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