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GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 593 AIRFOIL (goe593-il)
Reynolds number: 500,000
Max Cl/Cd: 101.39 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe593-il-500000.txt
Download as CSV file: xf-goe593-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 593 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5917   0.05168   0.04938  -0.0715   0.9949   0.0220
 -10.000  -0.5920   0.04404   0.04142  -0.0799   0.9871   0.0224
  -9.250  -0.5446   0.03300   0.02955  -0.0882   0.9735   0.0243
  -9.000  -0.5402   0.02808   0.02396  -0.0877   0.9658   0.0251
  -8.750  -0.5161   0.02589   0.02125  -0.0885   0.9623   0.0259
  -8.500  -0.4912   0.02296   0.01810  -0.0898   0.9603   0.0268
  -8.250  -0.4656   0.02245   0.01757  -0.0898   0.9556   0.0276
  -8.000  -0.4376   0.02167   0.01671  -0.0902   0.9517   0.0287
  -7.750  -0.4069   0.02047   0.01526  -0.0912   0.9493   0.0300
  -7.500  -0.3732   0.01965   0.01416  -0.0925   0.9476   0.0309
  -7.250  -0.3417   0.01753   0.01192  -0.0941   0.9462   0.0323
  -7.000  -0.3167   0.01702   0.01138  -0.0937   0.9403   0.0334
  -6.750  -0.2837   0.01636   0.01063  -0.0948   0.9370   0.0348
  -6.500  -0.2483   0.01561   0.00975  -0.0964   0.9343   0.0361
  -6.250  -0.2124   0.01472   0.00871  -0.0981   0.9320   0.0371
  -6.000  -0.1866   0.01376   0.00774  -0.0979   0.9254   0.0387
  -5.750  -0.1539   0.01327   0.00722  -0.0989   0.9205   0.0404
  -5.500  -0.1175   0.01271   0.00659  -0.1007   0.9167   0.0419
  -5.250  -0.0915   0.01236   0.00617  -0.1002   0.9084   0.0432
  -5.000  -0.0603   0.01168   0.00542  -0.1009   0.9024   0.0448
  -4.750  -0.0348   0.01122   0.00496  -0.1004   0.8940   0.0467
  -4.500  -0.0054   0.01088   0.00457  -0.1006   0.8867   0.0486
  -4.250   0.0199   0.01062   0.00426  -0.0999   0.8776   0.0506
  -4.000   0.0482   0.01029   0.00387  -0.0998   0.8695   0.0531
  -3.750   0.0709   0.00998   0.00356  -0.0986   0.8590   0.0568
  -3.500   0.0976   0.00977   0.00329  -0.0982   0.8492   0.0609
  -3.250   0.1226   0.00948   0.00300  -0.0974   0.8377   0.0697
  -3.000   0.1456   0.00921   0.00281  -0.0962   0.8249   0.0937
  -2.750   0.1702   0.00903   0.00269  -0.0954   0.8131   0.1205
  -2.500   0.1961   0.00892   0.00257  -0.0948   0.8029   0.1377
  -2.250   0.2211   0.00881   0.00244  -0.0941   0.7917   0.1529
  -2.000   0.2457   0.00869   0.00234  -0.0933   0.7806   0.1711
  -1.750   0.2703   0.00853   0.00225  -0.0925   0.7699   0.2026
  -1.500   0.2939   0.00832   0.00218  -0.0916   0.7590   0.2623
  -1.250   0.3162   0.00805   0.00212  -0.0905   0.7477   0.3368
  -1.000   0.3337   0.00749   0.00210  -0.0885   0.7370   0.5195
  -0.750   0.3471   0.00691   0.00213  -0.0852   0.7266   0.7110
  -0.500   0.3705   0.00656   0.00228  -0.0836   0.7163   0.8738
  -0.250   0.4229   0.00667   0.00238  -0.0886   0.7060   0.9310
   0.000   0.4656   0.00681   0.00243  -0.0915   0.6953   0.9524
   0.250   0.5080   0.00696   0.00251  -0.0945   0.6845   0.9665
   0.500   0.5515   0.00711   0.00257  -0.0977   0.6739   0.9760
   1.000   0.6382   0.00738   0.00267  -0.1042   0.6490   0.9914
   1.250   0.6882   0.00747   0.00268  -0.1090   0.6357   0.9982
   1.500   0.7179   0.00753   0.00268  -0.1095   0.6232   1.0000
   1.750   0.7372   0.00761   0.00269  -0.1078   0.6108   1.0000
   2.000   0.7563   0.00770   0.00271  -0.1059   0.5973   1.0000
   2.250   0.7751   0.00780   0.00274  -0.1040   0.5823   1.0000
   2.500   0.7938   0.00791   0.00279  -0.1021   0.5657   1.0000
   2.750   0.8123   0.00804   0.00285  -0.1001   0.5477   1.0000
   3.000   0.8304   0.00819   0.00292  -0.0981   0.5280   1.0000
   3.250   0.8475   0.00838   0.00302  -0.0958   0.5064   1.0000
   3.500   0.8644   0.00859   0.00313  -0.0936   0.4842   1.0000
   3.750   0.8810   0.00884   0.00327  -0.0913   0.4612   1.0000
   4.000   0.8973   0.00911   0.00342  -0.0889   0.4399   1.0000
   4.250   0.9145   0.00938   0.00360  -0.0867   0.4195   1.0000
   4.500   0.9317   0.00965   0.00378  -0.0846   0.4013   1.0000
   4.750   0.9492   0.00992   0.00398  -0.0825   0.3850   1.0000
   5.000   0.9671   0.01019   0.00418  -0.0805   0.3705   1.0000
   5.250   0.9849   0.01046   0.00439  -0.0785   0.3566   1.0000
   5.500   1.0026   0.01074   0.00461  -0.0765   0.3436   1.0000
   5.750   1.0205   0.01102   0.00483  -0.0746   0.3322   1.0000
   6.000   1.0397   0.01125   0.00504  -0.0729   0.3223   1.0000
   6.250   1.0572   0.01154   0.00530  -0.0709   0.3139   1.0000
   6.500   1.0763   0.01176   0.00552  -0.0692   0.3051   1.0000
   6.750   1.0928   0.01204   0.00577  -0.0670   0.2971   1.0000
   7.000   1.1103   0.01226   0.00601  -0.0650   0.2891   1.0000
   7.250   1.1267   0.01255   0.00627  -0.0629   0.2821   1.0000
   7.500   1.1446   0.01278   0.00651  -0.0610   0.2737   1.0000
   7.750   1.1614   0.01307   0.00679  -0.0590   0.2664   1.0000
   8.000   1.1799   0.01332   0.00707  -0.0574   0.2590   1.0000
   8.250   1.1964   0.01366   0.00739  -0.0554   0.2527   1.0000
   8.500   1.2158   0.01389   0.00768  -0.0539   0.2461   1.0000
   9.000   1.2511   0.01453   0.00835  -0.0505   0.2307   1.0000
   9.250   1.2672   0.01492   0.00872  -0.0487   0.2215   1.0000
   9.500   1.2832   0.01533   0.00911  -0.0468   0.2096   1.0000
   9.750   1.2983   0.01580   0.00955  -0.0449   0.1944   1.0000
  10.000   1.3123   0.01635   0.01005  -0.0429   0.1729   1.0000
  10.250   1.3184   0.01734   0.01082  -0.0399   0.1372   1.0000
  10.500   1.3180   0.01875   0.01197  -0.0362   0.1006   1.0000
  10.750   1.3230   0.01992   0.01304  -0.0333   0.0832   1.0000
  11.000   1.3311   0.02093   0.01403  -0.0309   0.0747   1.0000
  11.250   1.3394   0.02197   0.01507  -0.0287   0.0690   1.0000
  11.500   1.3489   0.02296   0.01610  -0.0267   0.0648   1.0000
  11.750   1.3586   0.02397   0.01716  -0.0249   0.0613   1.0000
  12.000   1.3651   0.02521   0.01842  -0.0229   0.0579   1.0000
  12.250   1.3734   0.02638   0.01966  -0.0212   0.0550   1.0000
  12.500   1.3837   0.02746   0.02082  -0.0198   0.0524   1.0000
  12.750   1.3903   0.02884   0.02223  -0.0182   0.0497   1.0000
  13.000   1.3914   0.03070   0.02414  -0.0164   0.0470   1.0000
  13.250   1.4032   0.03178   0.02531  -0.0154   0.0446   1.0000
  13.500   1.4095   0.03334   0.02692  -0.0143   0.0420   1.0000
  13.750   1.4087   0.03558   0.02919  -0.0129   0.0392   1.0000
  14.000   1.4185   0.03694   0.03066  -0.0122   0.0367   1.0000
  14.250   1.4215   0.03899   0.03274  -0.0113   0.0342   1.0000
  14.500   1.4212   0.04143   0.03525  -0.0105   0.0319   1.0000
  14.750   1.4243   0.04362   0.03752  -0.0099   0.0299   1.0000
  15.000   1.4226   0.04640   0.04035  -0.0095   0.0282   1.0000
  15.250   1.4163   0.04978   0.04380  -0.0092   0.0269   1.0000
  15.500   1.4169   0.05250   0.04663  -0.0091   0.0255   1.0000
  15.750   1.4143   0.05566   0.04989  -0.0091   0.0245   1.0000
  16.000   1.4102   0.05912   0.05342  -0.0094   0.0235   1.0000
  16.250   1.3994   0.06351   0.05789  -0.0100   0.0228   1.0000
  16.500   1.3897   0.06789   0.06238  -0.0107   0.0221   1.0000
  16.750   1.3836   0.07193   0.06654  -0.0115   0.0214   1.0000
  17.000   1.3784   0.07590   0.07062  -0.0124   0.0207   1.0000
  17.250   1.3700   0.08039   0.07521  -0.0135   0.0202   1.0000
  17.500   1.3616   0.08496   0.07988  -0.0148   0.0198   1.0000
  17.750   1.3518   0.08980   0.08481  -0.0162   0.0195   1.0000
  18.000   1.3400   0.09496   0.09004  -0.0178   0.0190   1.0000
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