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GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 723 AIRFOIL (goe723-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.59 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe723-il-1000000.txt
Download as CSV file: xf-goe723-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 723 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3176   0.08600   0.08430  -0.0490   0.9975   0.0254
  -9.000  -0.3033   0.08139   0.07969  -0.0543   0.9936   0.0260
  -8.750  -0.3840   0.03703   0.03461  -0.1104   0.9487   0.0285
  -8.500  -0.3425   0.03438   0.03192  -0.1165   0.9400   0.0288
  -8.250  -0.3007   0.03185   0.02924  -0.1230   0.9237   0.0292
  -8.000  -0.2726   0.02964   0.02678  -0.1262   0.8979   0.0296
  -7.750  -0.2553   0.02809   0.02500  -0.1261   0.8745   0.0302
  -7.500  -0.2396   0.02666   0.02333  -0.1253   0.8538   0.0311
  -7.250  -0.2178   0.02759   0.02384  -0.1239   0.8352   0.0330
  -7.000  -0.2016   0.02629   0.02225  -0.1227   0.8192   0.0331
  -6.750  -0.1971   0.02095   0.01651  -0.1213   0.8044   0.0341
  -6.500  -0.1756   0.01988   0.01535  -0.1205   0.7913   0.0344
  -6.000  -0.1389   0.01496   0.00955  -0.1171   0.7679   0.0286
  -5.750  -0.1155   0.01411   0.00858  -0.1163   0.7580   0.0287
  -5.500  -0.0915   0.01342   0.00778  -0.1155   0.7485   0.0289
  -5.250  -0.0670   0.01280   0.00709  -0.1149   0.7399   0.0290
  -5.000  -0.0423   0.01230   0.00651  -0.1142   0.7311   0.0292
  -4.750  -0.0172   0.01183   0.00599  -0.1136   0.7232   0.0294
  -4.500   0.0079   0.01141   0.00550  -0.1129   0.7155   0.0296
  -4.250   0.0332   0.01101   0.00506  -0.1123   0.7086   0.0298
  -4.000   0.0587   0.01065   0.00465  -0.1117   0.7013   0.0300
  -3.750   0.0838   0.01034   0.00428  -0.1111   0.6944   0.0302
  -3.500   0.1097   0.01002   0.00395  -0.1105   0.6877   0.0306
  -3.250   0.1354   0.00978   0.00366  -0.1100   0.6811   0.0311
  -3.000   0.1615   0.00957   0.00342  -0.1095   0.6750   0.0317
  -2.750   0.1876   0.00935   0.00316  -0.1090   0.6684   0.0321
  -2.500   0.2134   0.00918   0.00293  -0.1084   0.6618   0.0325
  -2.250   0.2401   0.00901   0.00275  -0.1080   0.6554   0.0329
  -2.000   0.2662   0.00889   0.00257  -0.1074   0.6475   0.0331
  -1.750   0.2917   0.00860   0.00224  -0.1068   0.6399   0.0338
  -1.500   0.3177   0.00843   0.00201  -0.1063   0.6320   0.0346
  -1.250   0.3442   0.00831   0.00187  -0.1058   0.6259   0.0356
  -1.000   0.3711   0.00821   0.00176  -0.1055   0.6197   0.0365
  -0.750   0.3976   0.00815   0.00166  -0.1050   0.6134   0.0378
  -0.500   0.4247   0.00809   0.00159  -0.1047   0.6076   0.0392
  -0.250   0.4515   0.00800   0.00149  -0.1043   0.6016   0.0428
   0.000   0.4778   0.00796   0.00143  -0.1038   0.5955   0.0492
   0.250   0.5009   0.00728   0.00136  -0.1030   0.5900   0.2517
   0.500   0.5264   0.00710   0.00140  -0.1025   0.5839   0.3353
   0.750   0.5525   0.00708   0.00144  -0.1020   0.5782   0.3715
   1.000   0.5795   0.00703   0.00148  -0.1017   0.5727   0.4012
   1.250   0.6057   0.00701   0.00152  -0.1012   0.5664   0.4336
   1.500   0.6319   0.00701   0.00156  -0.1008   0.5589   0.4617
   1.750   0.6576   0.00701   0.00161  -0.1002   0.5488   0.4904
   2.000   0.6834   0.00699   0.00167  -0.0997   0.5397   0.5302
   2.250   0.7085   0.00697   0.00174  -0.0990   0.5320   0.5751
   2.500   0.7331   0.00687   0.00181  -0.0982   0.5245   0.6419
   2.750   0.8355   0.00636   0.00201  -0.1151   0.5094   1.0000
   3.000   0.8612   0.00647   0.00208  -0.1146   0.5004   1.0000
   3.250   0.8870   0.00658   0.00215  -0.1140   0.4901   1.0000
   3.500   0.9121   0.00672   0.00224  -0.1134   0.4793   1.0000
   3.750   0.9370   0.00686   0.00233  -0.1127   0.4664   1.0000
   4.000   0.9614   0.00704   0.00243  -0.1119   0.4497   1.0000
   4.250   0.9857   0.00723   0.00255  -0.1111   0.4320   1.0000
   4.500   1.0095   0.00744   0.00269  -0.1102   0.4126   1.0000
   4.750   1.0324   0.00770   0.00285  -0.1092   0.3906   1.0000
   5.000   1.0546   0.00801   0.00305  -0.1080   0.3672   1.0000
   5.250   1.0754   0.00840   0.00329  -0.1067   0.3392   1.0000
   5.500   1.0960   0.00879   0.00354  -0.1053   0.3110   1.0000
   5.750   1.1165   0.00920   0.00382  -0.1038   0.2837   1.0000
   6.000   1.1339   0.00977   0.00417  -0.1019   0.2436   1.0000
   6.250   1.1340   0.01137   0.00511  -0.0971   0.1272   1.0000
   6.500   1.1488   0.01207   0.00564  -0.0947   0.0937   1.0000
   6.750   1.1652   0.01266   0.00608  -0.0927   0.0697   1.0000
   7.000   1.1848   0.01305   0.00642  -0.0912   0.0631   1.0000
   7.250   1.2036   0.01347   0.00681  -0.0895   0.0587   1.0000
   7.500   1.2232   0.01383   0.00718  -0.0880   0.0563   1.0000
   7.750   1.2433   0.01414   0.00751  -0.0866   0.0550   1.0000
   8.000   1.2625   0.01449   0.00789  -0.0851   0.0534   1.0000
   8.250   1.2791   0.01489   0.00830  -0.0830   0.0515   1.0000
   8.500   1.2924   0.01536   0.00878  -0.0804   0.0494   1.0000
   8.750   1.3050   0.01587   0.00933  -0.0777   0.0477   1.0000
   9.000   1.3224   0.01620   0.00968  -0.0760   0.0471   1.0000
   9.250   1.3391   0.01657   0.01009  -0.0741   0.0461   1.0000
   9.500   1.3549   0.01701   0.01056  -0.0722   0.0451   1.0000
   9.750   1.3705   0.01747   0.01105  -0.0704   0.0438   1.0000
  10.000   1.3844   0.01804   0.01163  -0.0683   0.0427   1.0000
  10.250   1.3954   0.01879   0.01240  -0.0660   0.0413   1.0000
  10.500   1.4050   0.01965   0.01332  -0.0636   0.0401   1.0000
  10.750   1.4231   0.02006   0.01377  -0.0625   0.0394   1.0000
  11.000   1.4385   0.02065   0.01439  -0.0610   0.0384   1.0000
  11.250   1.4531   0.02130   0.01508  -0.0596   0.0373   1.0000
  11.500   1.4667   0.02206   0.01585  -0.0581   0.0362   1.0000
  11.750   1.4776   0.02302   0.01683  -0.0565   0.0350   1.0000
  12.000   1.4851   0.02428   0.01814  -0.0546   0.0338   1.0000
  12.250   1.5012   0.02495   0.01886  -0.0537   0.0329   1.0000
  12.500   1.5155   0.02578   0.01973  -0.0526   0.0317   1.0000
  12.750   1.5279   0.02679   0.02075  -0.0515   0.0304   1.0000
  13.000   1.5358   0.02819   0.02216  -0.0502   0.0290   1.0000
  13.250   1.5458   0.02946   0.02349  -0.0491   0.0279   1.0000
  13.500   1.5570   0.03066   0.02474  -0.0481   0.0268   1.0000
  13.750   1.5662   0.03206   0.02616  -0.0472   0.0255   1.0000
  14.000   1.5710   0.03389   0.02802  -0.0461   0.0243   1.0000
  14.250   1.5773   0.03563   0.02983  -0.0451   0.0234   1.0000
  14.500   1.5848   0.03727   0.03153  -0.0443   0.0224   1.0000
  14.750   1.5903   0.03913   0.03342  -0.0435   0.0214   1.0000
  15.000   1.5922   0.04141   0.03573  -0.0427   0.0203   1.0000
  15.250   1.5927   0.04388   0.03827  -0.0419   0.0197   1.0000
  15.500   1.5966   0.04603   0.04051  -0.0413   0.0192   1.0000
  15.750   1.5990   0.04840   0.04295  -0.0408   0.0186   1.0000
  16.000   1.6006   0.05091   0.04552  -0.0404   0.0181   1.0000
  16.250   1.6001   0.05370   0.04836  -0.0400   0.0175   1.0000
  16.500   1.5966   0.05691   0.05163  -0.0398   0.0170   1.0000
  16.750   1.5904   0.06053   0.05533  -0.0397   0.0165   1.0000
  17.000   1.5913   0.06335   0.05824  -0.0396   0.0163   1.0000
  17.250   1.5910   0.06633   0.06130  -0.0397   0.0159   1.0000
  17.500   1.5897   0.06948   0.06454  -0.0398   0.0155   1.0000
  17.750   1.5876   0.07280   0.06794  -0.0400   0.0152   1.0000
  18.000   1.5845   0.07630   0.07153  -0.0404   0.0150   1.0000
  18.250   1.5809   0.07989   0.07517  -0.0408   0.0146   1.0000
  18.500   1.5759   0.08371   0.07907  -0.0414   0.0144   1.0000
  18.750   1.5671   0.08814   0.08358  -0.0422   0.0140   1.0000
  19.000   1.5564   0.09293   0.08846  -0.0432   0.0137   1.0000
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