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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.49 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe553-il-1000000.txt
Download as CSV file: xf-goe553-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2210   0.09843   0.09686  -0.0450   0.9987   0.0257
 -11.000  -0.2227   0.09215   0.09058  -0.0483   0.9909   0.0258
 -10.750  -0.3124   0.09877   0.09709  -0.0418   1.0000   0.0257
 -10.500  -0.1992   0.08254   0.08095  -0.0555   0.9688   0.0263
 -10.250  -0.1636   0.07785   0.07620  -0.0634   0.9529   0.0267
 -10.000  -0.1238   0.07155   0.06978  -0.0743   0.9217   0.0275
  -9.750  -0.3924   0.05333   0.05165  -0.0765   0.9751   0.0263
  -9.500  -0.4313   0.02676   0.02361  -0.1131   0.9261   0.0252
  -9.250  -0.4129   0.02493   0.02133  -0.1134   0.8936   0.0257
  -9.000  -0.4054   0.02152   0.01739  -0.1125   0.8602   0.0261
  -8.750  -0.3869   0.02034   0.01598  -0.1115   0.8245   0.0264
  -8.500  -0.3663   0.01977   0.01520  -0.1105   0.7856   0.0267
  -8.250  -0.3445   0.01929   0.01453  -0.1096   0.7502   0.0270
  -8.000  -0.3218   0.01873   0.01379  -0.1089   0.7225   0.0273
  -7.750  -0.2985   0.01809   0.01297  -0.1084   0.7021   0.0276
  -7.500  -0.2745   0.01735   0.01207  -0.1079   0.6871   0.0279
  -7.250  -0.2499   0.01661   0.01116  -0.1075   0.6752   0.0283
  -7.000  -0.2248   0.01603   0.01042  -0.1070   0.6646   0.0288
  -6.750  -0.1989   0.01543   0.00969  -0.1067   0.6563   0.0292
  -6.500  -0.1731   0.01483   0.00895  -0.1063   0.6482   0.0295
  -6.250  -0.1465   0.01436   0.00837  -0.1061   0.6412   0.0297
  -6.000  -0.1196   0.01402   0.00793  -0.1058   0.6344   0.0299
  -5.750  -0.0945   0.01305   0.00683  -0.1054   0.6279   0.0304
  -5.500  -0.0682   0.01233   0.00610  -0.1051   0.6229   0.0308
  -5.250  -0.0413   0.01193   0.00567  -0.1049   0.6174   0.0312
  -5.000  -0.0143   0.01168   0.00538  -0.1046   0.6119   0.0318
  -4.750   0.0132   0.01140   0.00508  -0.1044   0.6072   0.0323
  -4.500   0.0407   0.01110   0.00475  -0.1042   0.6023   0.0328
  -4.250   0.0680   0.01081   0.00443  -0.1040   0.5973   0.0332
  -4.000   0.0951   0.01059   0.00414  -0.1037   0.5923   0.0337
  -3.750   0.1231   0.01033   0.00387  -0.1036   0.5883   0.0341
  -3.500   0.1510   0.01012   0.00364  -0.1034   0.5833   0.0345
  -3.250   0.1786   0.00995   0.00343  -0.1032   0.5781   0.0349
  -3.000   0.2056   0.00955   0.00299  -0.1030   0.5733   0.0358
  -2.750   0.2337   0.00935   0.00279  -0.1029   0.5688   0.0367
  -2.500   0.2618   0.00922   0.00264  -0.1028   0.5637   0.0378
  -2.250   0.2896   0.00912   0.00251  -0.1026   0.5582   0.0388
  -2.000   0.3180   0.00900   0.00237  -0.1026   0.5532   0.0397
  -1.750   0.3462   0.00887   0.00222  -0.1025   0.5472   0.0407
  -1.500   0.3739   0.00875   0.00206  -0.1023   0.5409   0.0428
  -1.250   0.4023   0.00865   0.00196  -0.1022   0.5347   0.0450
  -1.000   0.4304   0.00858   0.00186  -0.1021   0.5271   0.0480
  -0.750   0.4584   0.00849   0.00177  -0.1019   0.5196   0.0562
  -0.500   0.4856   0.00816   0.00169  -0.1019   0.5112   0.1394
  -0.250   0.5118   0.00762   0.00163  -0.1018   0.5034   0.3194
   0.000   0.5384   0.00730   0.00166  -0.1017   0.4946   0.4552
   0.250   0.5659   0.00727   0.00171  -0.1015   0.4861   0.5018
   0.500   0.5935   0.00729   0.00175  -0.1013   0.4768   0.5309
   0.750   0.6212   0.00733   0.00180  -0.1011   0.4681   0.5568
   1.250   0.6762   0.00745   0.00191  -0.1007   0.4491   0.5917
   1.500   0.7033   0.00753   0.00199  -0.1004   0.4397   0.6134
   1.750   0.7306   0.00758   0.00207  -0.1002   0.4309   0.6355
   2.000   0.7577   0.00767   0.00215  -0.0999   0.4220   0.6510
   2.250   0.7851   0.00775   0.00222  -0.0998   0.4138   0.6635
   2.500   0.8121   0.00784   0.00231  -0.0995   0.4059   0.6773
   2.750   0.8393   0.00791   0.00239  -0.0993   0.3983   0.6925
   3.000   0.8658   0.00801   0.00250  -0.0989   0.3911   0.7134
   3.250   0.8926   0.00803   0.00260  -0.0986   0.3850   0.7407
   3.500   0.9184   0.00808   0.00271  -0.0982   0.3784   0.7763
   3.750   0.9423   0.00800   0.00282  -0.0972   0.3726   0.8446
   4.000   0.9789   0.00792   0.00293  -0.0990   0.3654   1.0000
   4.250   1.0053   0.00810   0.00306  -0.0988   0.3589   1.0000
   4.500   1.0327   0.00821   0.00316  -0.0986   0.3538   1.0000
   4.750   1.0593   0.00837   0.00328  -0.0984   0.3479   1.0000
   5.000   1.0856   0.00855   0.00343  -0.0981   0.3422   1.0000
   5.250   1.1126   0.00867   0.00355  -0.0979   0.3377   1.0000
   5.500   1.1389   0.00883   0.00369  -0.0976   0.3326   1.0000
   5.750   1.1646   0.00904   0.00386  -0.0972   0.3270   1.0000
   6.000   1.1914   0.00916   0.00399  -0.0971   0.3227   1.0000
   6.250   1.2171   0.00935   0.00415  -0.0967   0.3154   1.0000
   6.500   1.2426   0.00955   0.00433  -0.0963   0.3089   1.0000
   6.750   1.2684   0.00972   0.00449  -0.0960   0.3022   1.0000
   7.000   1.2931   0.00996   0.00470  -0.0955   0.2946   1.0000
   7.250   1.3187   0.01013   0.00487  -0.0951   0.2878   1.0000
   7.500   1.3427   0.01040   0.00510  -0.0945   0.2791   1.0000
   7.750   1.3674   0.01062   0.00530  -0.0940   0.2703   1.0000
   8.000   1.3908   0.01090   0.00555  -0.0934   0.2592   1.0000
   8.250   1.4130   0.01126   0.00584  -0.0925   0.2443   1.0000
   8.500   1.4339   0.01168   0.00617  -0.0915   0.2272   1.0000
   8.750   1.4529   0.01219   0.00657  -0.0902   0.2086   1.0000
   9.000   1.4713   0.01271   0.00701  -0.0887   0.1936   1.0000
   9.250   1.4907   0.01314   0.00740  -0.0874   0.1846   1.0000
   9.500   1.5091   0.01360   0.00783  -0.0860   0.1771   1.0000
   9.750   1.5288   0.01395   0.00819  -0.0848   0.1727   1.0000
  10.000   1.5447   0.01440   0.00863  -0.0829   0.1670   1.0000
  10.250   1.5602   0.01479   0.00903  -0.0809   0.1620   1.0000
  10.500   1.5759   0.01518   0.00943  -0.0790   0.1577   1.0000
  10.750   1.5884   0.01570   0.00994  -0.0767   0.1525   1.0000
  11.000   1.6034   0.01613   0.01040  -0.0748   0.1484   1.0000
  11.250   1.6192   0.01654   0.01083  -0.0731   0.1442   1.0000
  11.500   1.6306   0.01716   0.01145  -0.0709   0.1383   1.0000
  11.750   1.6441   0.01770   0.01202  -0.0690   0.1323   1.0000
  12.000   1.6521   0.01855   0.01281  -0.0666   0.1201   1.0000
  12.250   1.6401   0.02051   0.01454  -0.0621   0.0878   1.0000
  12.500   1.6337   0.02239   0.01636  -0.0588   0.0750   1.0000
  12.750   1.6338   0.02404   0.01803  -0.0565   0.0687   1.0000
  13.000   1.6370   0.02563   0.01965  -0.0548   0.0649   1.0000
  13.250   1.6375   0.02754   0.02159  -0.0531   0.0607   1.0000
  13.500   1.6430   0.02919   0.02329  -0.0520   0.0583   1.0000
  13.750   1.6454   0.03120   0.02535  -0.0510   0.0559   1.0000
  14.000   1.6462   0.03346   0.02765  -0.0501   0.0534   1.0000
  14.250   1.6497   0.03556   0.02982  -0.0495   0.0516   1.0000
  14.500   1.6527   0.03777   0.03209  -0.0490   0.0498   1.0000
  14.750   1.6524   0.04034   0.03471  -0.0486   0.0478   1.0000
  15.000   1.6500   0.04321   0.03763  -0.0482   0.0460   1.0000
  15.250   1.6508   0.04580   0.04029  -0.0480   0.0445   1.0000
  15.500   1.6512   0.04846   0.04303  -0.0478   0.0430   1.0000
  15.750   1.6486   0.05153   0.04616  -0.0478   0.0414   1.0000
  16.000   1.6438   0.05495   0.04962  -0.0479   0.0398   1.0000
  16.250   1.6405   0.05827   0.05301  -0.0481   0.0382   1.0000
  16.500   1.6383   0.06155   0.05636  -0.0484   0.0366   1.0000
  16.750   1.6333   0.06528   0.06016  -0.0490   0.0351   1.0000
  17.000   1.6251   0.06951   0.06444  -0.0497   0.0334   1.0000
  17.250   1.6219   0.07318   0.06819  -0.0504   0.0320   1.0000
  17.500   1.6160   0.07730   0.07238  -0.0514   0.0304   1.0000
  17.750   1.6068   0.08197   0.07711  -0.0526   0.0289   1.0000
  18.000   1.6004   0.08634   0.08156  -0.0538   0.0275   1.0000
  18.250   1.5931   0.09091   0.08620  -0.0551   0.0260   1.0000
  18.500   1.5834   0.09596   0.09131  -0.0568   0.0248   1.0000
  18.750   1.5740   0.10101   0.09644  -0.0586   0.0237   1.0000
  19.000   1.5661   0.10590   0.10142  -0.0604   0.0226   1.0000
  19.250   1.5571   0.11105   0.10664  -0.0624   0.0217   1.0000
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