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GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 546 AIRFOIL (goe546-il)
Reynolds number: 200,000
Max Cl/Cd: 76.21 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe546-il-200000-n5.txt
Download as CSV file: xf-goe546-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 546 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4137   0.08588   0.08226  -0.0446   1.0000   0.0224
  -9.250  -0.4283   0.08109   0.07754  -0.0455   1.0000   0.0227
  -9.000  -0.4507   0.07642   0.07297  -0.0456   1.0000   0.0229
  -8.750  -0.4753   0.06909   0.06575  -0.0503   0.9959   0.0232
  -8.500  -0.5060   0.03930   0.03493  -0.0832   0.9745   0.0239
  -8.250  -0.4813   0.03808   0.03363  -0.0848   0.9678   0.0246
  -8.000  -0.4544   0.03558   0.03088  -0.0877   0.9635   0.0255
  -7.750  -0.4362   0.03212   0.02699  -0.0890   0.9555   0.0267
  -7.500  -0.4119   0.02798   0.02208  -0.0912   0.9515   0.0290
  -7.250  -0.3900   0.02587   0.01961  -0.0914   0.9456   0.0303
  -7.000  -0.3616   0.02467   0.01827  -0.0924   0.9417   0.0314
  -6.750  -0.3302   0.02360   0.01701  -0.0938   0.9389   0.0329
  -6.500  -0.2992   0.02235   0.01548  -0.0950   0.9359   0.0350
  -6.250  -0.2736   0.02114   0.01394  -0.0949   0.9303   0.0363
  -6.000  -0.2435   0.01983   0.01240  -0.0957   0.9265   0.0376
  -5.750  -0.2113   0.01894   0.01147  -0.0970   0.9235   0.0394
  -5.500  -0.1812   0.01818   0.01060  -0.0977   0.9196   0.0408
  -5.250  -0.1532   0.01742   0.00972  -0.0978   0.9143   0.0421
  -5.000  -0.1217   0.01673   0.00891  -0.0986   0.9103   0.0438
  -4.750  -0.0882   0.01612   0.00816  -0.0998   0.9071   0.0456
  -4.500  -0.0621   0.01551   0.00749  -0.0995   0.9009   0.0467
  -4.250  -0.0334   0.01479   0.00677  -0.0998   0.8958   0.0483
  -4.000  -0.0015   0.01426   0.00621  -0.1007   0.8917   0.0501
  -3.750   0.0240   0.01392   0.00584  -0.1002   0.8847   0.0523
  -3.500   0.0530   0.01357   0.00544  -0.1004   0.8791   0.0553
  -3.250   0.0821   0.01323   0.00503  -0.1006   0.8736   0.0580
  -3.000   0.1078   0.01286   0.00467  -0.1002   0.8661   0.0620
  -2.750   0.1381   0.01258   0.00432  -0.1005   0.8606   0.0677
  -2.500   0.1628   0.01232   0.00406  -0.0998   0.8516   0.0762
  -2.250   0.1918   0.01199   0.00376  -0.1000   0.8443   0.0965
  -2.000   0.2154   0.01148   0.00357  -0.0993   0.8343   0.1727
  -1.750   0.2407   0.01093   0.00345  -0.0990   0.8260   0.3058
  -1.500   0.2660   0.01065   0.00340  -0.0984   0.8172   0.3834
  -1.250   0.2913   0.01043   0.00339  -0.0978   0.8085   0.4566
  -1.000   0.3166   0.01018   0.00337  -0.0972   0.8000   0.5347
  -0.750   0.3396   0.00991   0.00339  -0.0959   0.7903   0.6115
  -0.500   0.3637   0.00964   0.00335  -0.0948   0.7816   0.6845
  -0.250   0.3870   0.00939   0.00335  -0.0934   0.7715   0.7640
   0.000   0.4192   0.00919   0.00334  -0.0937   0.7619   0.8692
   0.250   0.4742   0.00908   0.00322  -0.0992   0.7529   0.9639
   0.500   0.5099   0.00912   0.00318  -0.1009   0.7416   1.0000
   0.750   0.5349   0.00919   0.00316  -0.1002   0.7300   1.0000
   1.000   0.5601   0.00926   0.00315  -0.0995   0.7180   1.0000
   1.250   0.5852   0.00934   0.00313  -0.0988   0.7045   1.0000
   1.500   0.6102   0.00944   0.00314  -0.0981   0.6901   1.0000
   1.750   0.6352   0.00956   0.00316  -0.0973   0.6757   1.0000
   2.000   0.6601   0.00970   0.00319  -0.0966   0.6614   1.0000
   2.500   0.7093   0.01002   0.00336  -0.0950   0.6326   1.0000
   2.750   0.7338   0.01019   0.00347  -0.0943   0.6185   1.0000
   3.000   0.7579   0.01038   0.00360  -0.0934   0.6029   1.0000
   3.250   0.7816   0.01057   0.00373  -0.0925   0.5857   1.0000
   3.500   0.8050   0.01078   0.00388  -0.0915   0.5674   1.0000
   3.750   0.8284   0.01097   0.00405  -0.0905   0.5491   1.0000
   4.000   0.8512   0.01118   0.00421  -0.0895   0.5275   1.0000
   4.250   0.8726   0.01145   0.00437  -0.0881   0.4989   1.0000
   4.500   0.8924   0.01179   0.00456  -0.0865   0.4645   1.0000
   4.750   0.9117   0.01219   0.00481  -0.0849   0.4312   1.0000
   5.000   0.9318   0.01258   0.00509  -0.0834   0.4019   1.0000
   5.250   0.9511   0.01302   0.00540  -0.0818   0.3695   1.0000
   5.500   0.9685   0.01358   0.00578  -0.0800   0.3253   1.0000
   5.750   0.9831   0.01432   0.00623  -0.0778   0.2716   1.0000
   6.000   0.9994   0.01501   0.00672  -0.0759   0.2350   1.0000
   6.250   1.0165   0.01566   0.00724  -0.0742   0.2041   1.0000
   6.750   1.0431   0.01749   0.00853  -0.0698   0.1068   1.0000
   7.000   1.0570   0.01835   0.00925  -0.0676   0.0805   1.0000
   7.250   1.0724   0.01909   0.00992  -0.0657   0.0636   1.0000
   7.500   1.0874   0.01975   0.01056  -0.0637   0.0554   1.0000
   7.750   1.1026   0.02038   0.01123  -0.0616   0.0517   1.0000
   8.000   1.1173   0.02102   0.01192  -0.0596   0.0492   1.0000
   8.250   1.1307   0.02175   0.01268  -0.0574   0.0471   1.0000
   8.500   1.1420   0.02260   0.01358  -0.0550   0.0451   1.0000
   8.750   1.1550   0.02336   0.01442  -0.0529   0.0438   1.0000
   9.000   1.1671   0.02419   0.01536  -0.0507   0.0425   1.0000
   9.250   1.1783   0.02509   0.01635  -0.0486   0.0414   1.0000
   9.500   1.1886   0.02608   0.01742  -0.0464   0.0402   1.0000
   9.750   1.1981   0.02716   0.01857  -0.0443   0.0390   1.0000
  10.000   1.2063   0.02838   0.01985  -0.0422   0.0378   1.0000
  10.250   1.2120   0.02986   0.02137  -0.0400   0.0366   1.0000
  10.500   1.2194   0.03132   0.02291  -0.0380   0.0357   1.0000
  10.750   1.2305   0.03249   0.02421  -0.0365   0.0347   1.0000
  11.000   1.2407   0.03377   0.02561  -0.0350   0.0336   1.0000
  11.250   1.2503   0.03514   0.02708  -0.0335   0.0325   1.0000
  11.500   1.2591   0.03661   0.02864  -0.0321   0.0313   1.0000
  11.750   1.2672   0.03814   0.03024  -0.0308   0.0302   1.0000
  12.000   1.2743   0.03988   0.03203  -0.0294   0.0291   1.0000
  12.250   1.2820   0.04199   0.03418  -0.0281   0.0280   1.0000
  12.500   1.2900   0.04357   0.03595  -0.0270   0.0272   1.0000
  12.750   1.2970   0.04532   0.03789  -0.0260   0.0262   1.0000
  13.000   1.3028   0.04724   0.03997  -0.0250   0.0252   1.0000
  13.250   1.3079   0.04927   0.04214  -0.0242   0.0242   1.0000
  13.500   1.3121   0.05142   0.04440  -0.0235   0.0234   1.0000
  13.750   1.3155   0.05368   0.04674  -0.0230   0.0227   1.0000
  14.000   1.3183   0.05609   0.04920  -0.0225   0.0221   1.0000
  14.250   1.3195   0.05887   0.05214  -0.0221   0.0215   1.0000
  14.500   1.3183   0.06190   0.05543  -0.0220   0.0208   1.0000
  14.750   1.3159   0.06518   0.05895  -0.0221   0.0200   1.0000
  15.000   1.3129   0.06866   0.06263  -0.0225   0.0194   1.0000
  15.250   1.3089   0.07238   0.06653  -0.0231   0.0189   1.0000
  15.500   1.3042   0.07630   0.07061  -0.0241   0.0184   1.0000
  15.750   1.2992   0.08037   0.07484  -0.0253   0.0180   1.0000
  16.000   1.2937   0.08467   0.07928  -0.0267   0.0177   1.0000
  16.250   1.2882   0.08909   0.08382  -0.0284   0.0174   1.0000
  16.500   1.2825   0.09367   0.08852  -0.0303   0.0172   1.0000
  16.750   1.2760   0.09849   0.09344  -0.0325   0.0169   1.0000
  17.000   1.2626   0.10489   0.10005  -0.0356   0.0167   1.0000
  17.250   1.2444   0.11262   0.10805  -0.0397   0.0165   1.0000
  17.500   1.2258   0.12074   0.11639  -0.0443   0.0164   1.0000
  17.750   1.2054   0.12965   0.12553  -0.0497   0.0163   1.0000
  18.000   1.1808   0.14015   0.13626  -0.0564   0.0163   1.0000
  18.250   1.1556   0.15144   0.14773  -0.0637   0.0164   1.0000
  18.500   1.1209   0.16632   0.16278  -0.0733   0.0167   1.0000
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