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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 500,000
Max Cl/Cd: 107.86 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe549-il-500000.txt
Download as CSV file: xf-goe549-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 549 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2613   0.11139   0.10913  -0.0447   1.0000   0.0266
 -10.750  -0.2676   0.10694   0.10471  -0.0476   1.0000   0.0279
 -10.500  -0.2702   0.10337   0.10119  -0.0487   1.0000   0.0281
 -10.250  -0.2590   0.09809   0.09591  -0.0539   0.9910   0.0282
 -10.000  -0.2475   0.09309   0.09091  -0.0588   0.9789   0.0282
  -9.750  -0.2346   0.08722   0.08502  -0.0653   0.9656   0.0283
  -9.500  -0.2266   0.08004   0.07785  -0.0716   0.9552   0.0289
  -9.250  -0.1951   0.07660   0.07436  -0.0780   0.9453   0.0295
  -9.000  -0.1638   0.07164   0.06933  -0.0872   0.9316   0.0299
  -8.750  -0.1362   0.06646   0.06406  -0.0964   0.9112   0.0306
  -8.500  -0.1299   0.06137   0.05885  -0.1022   0.8856   0.0310
  -8.250  -0.1430   0.05621   0.05362  -0.1058   0.8611   0.0313
  -8.000  -0.1752   0.04788   0.04508  -0.1117   0.8383   0.0314
  -7.750  -0.1863   0.04311   0.04006  -0.1124   0.8203   0.0319
  -7.500  -0.1903   0.03894   0.03560  -0.1121   0.8027   0.0328
  -7.250  -0.2205   0.02753   0.02307  -0.1091   0.7867   0.0267
  -7.000  -0.2098   0.02454   0.01964  -0.1074   0.7685   0.0265
  -6.750  -0.1939   0.02251   0.01719  -0.1059   0.7492   0.0269
  -6.500  -0.1736   0.02150   0.01582  -0.1046   0.7301   0.0278
  -6.250  -0.1565   0.01937   0.01324  -0.1032   0.7135   0.0290
  -6.000  -0.1349   0.01810   0.01181  -0.1025   0.6995   0.0301
  -5.750  -0.1110   0.01749   0.01111  -0.1019   0.6880   0.0313
  -5.500  -0.0868   0.01687   0.01031  -0.1013   0.6785   0.0326
  -5.250  -0.0617   0.01637   0.00966  -0.1008   0.6701   0.0340
  -5.000  -0.0357   0.01630   0.00941  -0.1003   0.6631   0.0352
  -4.750  -0.0117   0.01503   0.00798  -0.0997   0.6566   0.0365
  -4.500   0.0128   0.01422   0.00710  -0.0992   0.6508   0.0380
  -4.250   0.0386   0.01380   0.00665  -0.0989   0.6454   0.0395
  -4.000   0.0646   0.01342   0.00622  -0.0985   0.6400   0.0410
  -3.750   0.0903   0.01301   0.00572  -0.0980   0.6350   0.0415
  -3.500   0.1163   0.01263   0.00527  -0.0976   0.6304   0.0419
  -3.250   0.1423   0.01227   0.00487  -0.0971   0.6255   0.0423
  -3.000   0.1682   0.01199   0.00452  -0.0967   0.6208   0.0427
  -2.750   0.1944   0.01177   0.00423  -0.0963   0.6161   0.0431
  -2.500   0.2207   0.01151   0.00395  -0.0959   0.6114   0.0436
  -2.250   0.2473   0.01134   0.00374  -0.0956   0.6067   0.0442
  -2.000   0.2736   0.01114   0.00345  -0.0952   0.6024   0.0453
  -1.750   0.3002   0.01094   0.00323  -0.0949   0.5983   0.0466
  -1.500   0.3271   0.01079   0.00307  -0.0946   0.5938   0.0484
  -1.250   0.3542   0.01069   0.00293  -0.0944   0.5896   0.0509
  -0.750   0.4072   0.01033   0.00277  -0.0939   0.5816   0.1214
  -0.500   0.4308   0.00973   0.00272  -0.0934   0.5773   0.2927
  -0.250   0.4552   0.00936   0.00272  -0.0929   0.5731   0.4150
   0.000   0.4791   0.00910   0.00282  -0.0921   0.5692   0.5508
   0.250   0.5041   0.00893   0.00286  -0.0915   0.5649   0.6152
   0.500   0.5292   0.00881   0.00288  -0.0909   0.5604   0.6678
   0.750   0.5531   0.00865   0.00290  -0.0899   0.5561   0.7316
   1.000   0.5773   0.00829   0.00299  -0.0888   0.5521   0.8757
   1.250   0.6726   0.00827   0.00301  -0.1033   0.5453   1.0000
   1.500   0.6971   0.00834   0.00301  -0.1026   0.5406   1.0000
   1.750   0.7218   0.00843   0.00305  -0.1020   0.5359   1.0000
   2.000   0.7466   0.00848   0.00309  -0.1013   0.5307   1.0000
   2.250   0.7713   0.00856   0.00311  -0.1007   0.5256   1.0000
   2.500   0.7960   0.00865   0.00316  -0.1000   0.5204   1.0000
   2.750   0.8209   0.00871   0.00321  -0.0994   0.5144   1.0000
   3.000   0.8454   0.00881   0.00325  -0.0987   0.5091   1.0000
   3.250   0.8702   0.00890   0.00333  -0.0981   0.5032   1.0000
   3.500   0.8948   0.00898   0.00340  -0.0975   0.4966   1.0000
   3.750   0.9190   0.00909   0.00347  -0.0967   0.4895   1.0000
   4.000   0.9429   0.00918   0.00353  -0.0960   0.4802   1.0000
   4.250   0.9671   0.00930   0.00362  -0.0953   0.4724   1.0000
   4.500   0.9904   0.00944   0.00371  -0.0944   0.4630   1.0000
   4.750   1.0147   0.00957   0.00383  -0.0938   0.4543   1.0000
   5.000   1.0379   0.00975   0.00396  -0.0929   0.4462   1.0000
   5.250   1.0620   0.00989   0.00411  -0.0923   0.4374   1.0000
   5.500   1.0849   0.01008   0.00426  -0.0914   0.4272   1.0000
   6.000   1.1304   0.01048   0.00460  -0.0897   0.4071   1.0000
   6.250   1.1527   0.01071   0.00481  -0.0887   0.3984   1.0000
   6.500   1.1743   0.01096   0.00502  -0.0877   0.3879   1.0000
   6.750   1.1966   0.01118   0.00524  -0.0868   0.3785   1.0000
   7.000   1.2174   0.01146   0.00549  -0.0856   0.3689   1.0000
   7.250   1.2391   0.01171   0.00573  -0.0846   0.3605   1.0000
   7.500   1.2599   0.01199   0.00600  -0.0835   0.3537   1.0000
   7.750   1.2809   0.01224   0.00626  -0.0824   0.3458   1.0000
   8.000   1.3004   0.01255   0.00657  -0.0811   0.3384   1.0000
   8.250   1.3201   0.01283   0.00686  -0.0798   0.3301   1.0000
   8.500   1.3378   0.01316   0.00718  -0.0781   0.3234   1.0000
   8.750   1.3551   0.01345   0.00749  -0.0764   0.3155   1.0000
   9.000   1.3702   0.01381   0.00785  -0.0743   0.3081   1.0000
   9.250   1.3873   0.01412   0.00820  -0.0726   0.3011   1.0000
   9.500   1.4015   0.01454   0.00861  -0.0705   0.2942   1.0000
   9.750   1.4189   0.01487   0.00900  -0.0690   0.2875   1.0000
  10.000   1.4318   0.01538   0.00949  -0.0668   0.2800   1.0000
  10.250   1.4470   0.01582   0.00997  -0.0651   0.2699   1.0000
  10.500   1.4594   0.01639   0.01054  -0.0630   0.2592   1.0000
  10.750   1.4701   0.01707   0.01121  -0.0609   0.2484   1.0000
  11.000   1.4794   0.01786   0.01199  -0.0586   0.2361   1.0000
  11.250   1.4863   0.01884   0.01292  -0.0563   0.2186   1.0000
  11.500   1.4890   0.02011   0.01413  -0.0537   0.1980   1.0000
  11.750   1.4861   0.02184   0.01573  -0.0508   0.1730   1.0000
  12.000   1.4783   0.02404   0.01779  -0.0479   0.1448   1.0000
  12.250   1.4633   0.02698   0.02055  -0.0449   0.1130   1.0000
  12.500   1.4510   0.02997   0.02344  -0.0426   0.0930   1.0000
  12.750   1.4487   0.03235   0.02582  -0.0412   0.0842   1.0000
  13.000   1.4453   0.03496   0.02845  -0.0400   0.0757   1.0000
  13.250   1.4414   0.03773   0.03124  -0.0390   0.0661   1.0000
  13.500   1.4367   0.04069   0.03418  -0.0382   0.0545   1.0000
  13.750   1.4279   0.04416   0.03760  -0.0376   0.0417   1.0000
  14.000   1.4200   0.04763   0.04107  -0.0370   0.0348   1.0000
  14.250   1.4130   0.05110   0.04458  -0.0367   0.0307   1.0000
  14.500   1.4089   0.05433   0.04788  -0.0364   0.0285   1.0000
  14.750   1.4032   0.05782   0.05143  -0.0363   0.0267   1.0000
  15.000   1.3967   0.06150   0.05518  -0.0363   0.0254   1.0000
  15.250   1.3928   0.06495   0.05873  -0.0364   0.0248   1.0000
  15.500   1.3892   0.06841   0.06230  -0.0366   0.0239   1.0000
  15.750   1.3849   0.07206   0.06603  -0.0369   0.0231   1.0000
  16.000   1.3796   0.07592   0.06998  -0.0374   0.0225   1.0000
  16.250   1.3722   0.08011   0.07427  -0.0380   0.0219   1.0000
  16.500   1.3645   0.08444   0.07867  -0.0387   0.0213   1.0000
  16.750   1.3535   0.08932   0.08364  -0.0397   0.0207   1.0000
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