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GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 380 AIRFOIL (goe380-il)
Reynolds number: 500,000
Max Cl/Cd: 103.44 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe380-il-500000.txt
Download as CSV file: xf-goe380-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 380 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3037   0.09080   0.08878  -0.0211   1.0000   0.0101
  -7.250  -0.3118   0.08922   0.08726  -0.0185   1.0000   0.0102
  -7.000  -0.3206   0.08772   0.08581  -0.0160   1.0000   0.0103
  -6.750  -0.3004   0.08380   0.08189  -0.0210   0.9974   0.0105
  -6.500  -0.2742   0.07957   0.07763  -0.0275   0.9937   0.0108
  -6.250  -0.2479   0.07543   0.07348  -0.0339   0.9890   0.0111
  -6.000  -0.2174   0.07109   0.06911  -0.0411   0.9850   0.0114
  -5.750  -0.1862   0.06684   0.06483  -0.0480   0.9800   0.0120
  -5.500  -0.1537   0.06265   0.06059  -0.0547   0.9742   0.0123
  -5.250  -0.1150   0.05818   0.05606  -0.0625   0.9705   0.0133
  -5.000  -0.0736   0.05430   0.05209  -0.0699   0.9633   0.0142
  -4.750  -0.0314   0.05053   0.04820  -0.0764   0.9571   0.0145
  -4.500   0.0004   0.04703   0.04459  -0.0800   0.9467   0.0146
  -4.250   0.0288   0.04145   0.03885  -0.0839   0.9345   0.0150
  -4.000   0.0513   0.03849   0.03581  -0.0852   0.9201   0.0158
  -3.750   0.0759   0.03619   0.03340  -0.0862   0.9040   0.0168
  -3.500   0.1022   0.03374   0.03078  -0.0870   0.8876   0.0183
  -3.250   0.1373   0.03203   0.02881  -0.0872   0.8707   0.0217
  -3.000   0.1592   0.02755   0.02401  -0.0871   0.8535   0.0227
  -2.750   0.1789   0.02639   0.02277  -0.0869   0.8353   0.0248
  -2.500   0.2033   0.02478   0.02094  -0.0863   0.8180   0.0271
  -2.250   0.2344   0.02404   0.01988  -0.0851   0.8003   0.0313
  -1.500   0.3032   0.01312   0.00758  -0.0805   0.7459   0.0196
  -1.250   0.3281   0.01118   0.00516  -0.0792   0.7243   0.0196
  -1.000   0.3529   0.01037   0.00406  -0.0781   0.7004   0.0207
  -0.750   0.3773   0.00983   0.00327  -0.0771   0.6756   0.0228
  -0.500   0.4010   0.00928   0.00254  -0.0760   0.6513   0.0251
  -0.250   0.4255   0.00910   0.00222  -0.0751   0.6293   0.0290
   0.000   0.4502   0.00894   0.00196  -0.0742   0.6098   0.0393
   0.250   0.4764   0.00912   0.00209  -0.0737   0.5932   0.0686
   0.500   0.5026   0.00927   0.00217  -0.0733   0.5790   0.0783
   0.750   0.5287   0.00938   0.00220  -0.0729   0.5663   0.0864
   1.000   0.5552   0.00955   0.00229  -0.0726   0.5544   0.0946
   1.250   0.5802   0.00944   0.00216  -0.0720   0.5425   0.1016
   1.500   0.6058   0.00947   0.00211  -0.0715   0.5300   0.1071
   1.750   0.6308   0.00940   0.00201  -0.0709   0.5174   0.1147
   2.000   0.6562   0.00942   0.00197  -0.0704   0.5053   0.1222
   2.250   0.6817   0.00941   0.00196  -0.0699   0.4928   0.1317
   2.500   0.7072   0.00941   0.00199  -0.0695   0.4799   0.1513
   2.750   0.7806   0.00793   0.00222  -0.0803   0.4592   1.0000
   3.000   0.8048   0.00807   0.00227  -0.0796   0.4440   1.0000
   3.250   0.8290   0.00823   0.00235  -0.0788   0.4287   1.0000
   3.500   0.8529   0.00840   0.00246  -0.0780   0.4134   1.0000
   3.750   0.8767   0.00859   0.00257  -0.0772   0.3987   1.0000
   4.000   0.9003   0.00879   0.00270  -0.0764   0.3850   1.0000
   4.250   0.9239   0.00900   0.00285  -0.0756   0.3725   1.0000
   4.500   0.9475   0.00922   0.00301  -0.0748   0.3621   1.0000
   4.750   0.9709   0.00945   0.00322  -0.0740   0.3527   1.0000
   5.000   0.9949   0.00964   0.00341  -0.0733   0.3440   1.0000
   5.250   1.0182   0.00988   0.00362  -0.0725   0.3355   1.0000
   5.500   1.0418   0.01009   0.00383  -0.0717   0.3269   1.0000
   5.750   1.0654   0.01030   0.00408  -0.0710   0.3189   1.0000
   6.000   1.0883   0.01055   0.00431  -0.0701   0.3070   1.0000
   6.250   1.1114   0.01079   0.00453  -0.0693   0.2924   1.0000
   6.500   1.1344   0.01103   0.00475  -0.0685   0.2762   1.0000
   6.750   1.1571   0.01130   0.00500  -0.0677   0.2590   1.0000
   7.000   1.1789   0.01165   0.00530  -0.0667   0.2354   1.0000
   7.250   1.1973   0.01229   0.00570  -0.0653   0.1915   1.0000
   7.500   1.2128   0.01322   0.00635  -0.0635   0.1476   1.0000
   7.750   1.2118   0.01567   0.00798  -0.0592   0.0263   1.0000
   8.000   1.2290   0.01645   0.00886  -0.0574   0.0184   1.0000
   8.250   1.2461   0.01721   0.00972  -0.0557   0.0153   1.0000
   8.500   1.2582   0.01839   0.01110  -0.0531   0.0133   1.0000
   8.750   1.2717   0.01933   0.01218  -0.0508   0.0126   1.0000
   9.000   1.2846   0.02024   0.01321  -0.0485   0.0120   1.0000
   9.250   1.2943   0.02131   0.01439  -0.0457   0.0113   1.0000
   9.500   1.2995   0.02242   0.01562  -0.0422   0.0107   1.0000
   9.750   1.3046   0.02345   0.01673  -0.0388   0.0102   1.0000
  10.000   1.3089   0.02456   0.01793  -0.0356   0.0096   1.0000
  10.250   1.3089   0.02604   0.01949  -0.0322   0.0091   1.0000
  10.500   1.3072   0.02775   0.02130  -0.0290   0.0088   1.0000
  10.750   1.3030   0.02986   0.02353  -0.0259   0.0085   1.0000
  11.000   1.2918   0.03299   0.02677  -0.0226   0.0081   1.0000
  11.250   1.2927   0.03547   0.02933  -0.0205   0.0081   1.0000
  11.500   1.2986   0.03831   0.03226  -0.0185   0.0079   1.0000
  11.750   1.3020   0.03991   0.03401  -0.0173   0.0077   1.0000
  12.000   1.3104   0.04247   0.03668  -0.0158   0.0078   1.0000
  12.250   1.3137   0.04478   0.03916  -0.0146   0.0076   1.0000
  12.500   1.3378   0.04804   0.04249  -0.0133   0.0082   1.0000
  12.750   1.3370   0.04981   0.04440  -0.0122   0.0084   1.0000
  17.250   0.8587   0.17362   0.17179  -0.0693   0.0203   1.0000
  17.500   0.8474   0.18198   0.18017  -0.0738   0.0202   1.0000
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