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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 50,000
Max Cl/Cd: 42.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe397-il-50000-n5.txt
Download as CSV file: xf-goe397-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3826   0.09953   0.09275  -0.0202   1.0000   0.0766
  -7.500  -0.3830   0.09779   0.09112  -0.0224   1.0000   0.0788
  -7.250  -0.3808   0.09659   0.09001  -0.0279   1.0000   0.0801
  -7.000  -0.3739   0.09307   0.08657  -0.0300   1.0000   0.0810
  -6.750  -0.3651   0.08796   0.08149  -0.0259   1.0000   0.0844
  -6.500  -0.3579   0.08493   0.07851  -0.0268   1.0000   0.0884
  -6.250  -0.3486   0.08314   0.07675  -0.0327   1.0000   0.0935
  -6.000  -0.3399   0.07965   0.07332  -0.0347   1.0000   0.0955
  -5.750  -0.3342   0.07595   0.06969  -0.0314   1.0000   0.1023
  -5.500  -0.3184   0.07389   0.06756  -0.0384   1.0000   0.1093
  -5.250  -0.3151   0.06994   0.06374  -0.0341   1.0000   0.1147
  -4.750  -0.2922   0.06404   0.05781  -0.0370   1.0000   0.1269
  -4.250  -0.2671   0.05833   0.05198  -0.0389   1.0000   0.1408
  -4.000  -0.2547   0.05570   0.04928  -0.0394   1.0000   0.1543
  -3.750  -0.2446   0.05316   0.04672  -0.0386   1.0000   0.1705
  -3.250  -0.1736   0.04392   0.03645  -0.0466   1.0000   0.0772
  -3.000  -0.1353   0.04026   0.03240  -0.0505   0.9936   0.0750
  -2.750  -0.0926   0.03716   0.02867  -0.0547   0.9864   0.0788
  -2.500  -0.0553   0.03427   0.02532  -0.0575   0.9789   0.0768
  -2.250  -0.0178   0.03181   0.02236  -0.0600   0.9713   0.0755
  -2.000   0.0204   0.02971   0.01973  -0.0623   0.9644   0.0751
  -1.750   0.0566   0.02812   0.01762  -0.0641   0.9564   0.0779
  -1.500   0.0914   0.02689   0.01607  -0.0659   0.9486   0.0843
  -1.250   0.1289   0.02565   0.01444  -0.0677   0.9415   0.0846
  -1.000   0.1631   0.02466   0.01313  -0.0689   0.9337   0.0849
  -0.750   0.2021   0.02381   0.01197  -0.0709   0.9272   0.0856
  -0.500   0.2378   0.02316   0.01106  -0.0723   0.9195   0.0870
  -0.250   0.2766   0.02258   0.01031  -0.0743   0.9131   0.0893
   0.000   0.3094   0.02219   0.00977  -0.0753   0.9043   0.0925
   0.250   0.3475   0.02177   0.00929  -0.0772   0.8976   0.0981
   0.500   0.3786   0.02152   0.00901  -0.0779   0.8872   0.1091
   0.750   0.4127   0.02101   0.00874  -0.0791   0.8771   0.1554
   1.250   0.4898   0.01914   0.00835  -0.0828   0.8576   1.0000
   1.500   0.5191   0.01933   0.00842  -0.0828   0.8456   1.0000
   1.750   0.5478   0.01954   0.00856  -0.0828   0.8339   1.0000
   2.000   0.5763   0.01975   0.00873  -0.0827   0.8226   1.0000
   2.250   0.6055   0.01995   0.00891  -0.0826   0.8117   1.0000
   2.500   0.6341   0.02016   0.00918  -0.0824   0.8007   1.0000
   2.750   0.6596   0.02045   0.00952  -0.0818   0.7882   1.0000
   3.000   0.6852   0.02075   0.00990  -0.0812   0.7759   1.0000
   3.250   0.7108   0.02105   0.01030  -0.0806   0.7635   1.0000
   3.500   0.7366   0.02133   0.01076  -0.0799   0.7510   1.0000
   3.750   0.7624   0.02162   0.01119  -0.0792   0.7384   1.0000
   4.000   0.7882   0.02189   0.01165  -0.0784   0.7256   1.0000
   4.250   0.8137   0.02217   0.01218  -0.0776   0.7123   1.0000
   4.500   0.8391   0.02247   0.01272  -0.0767   0.6987   1.0000
   4.750   0.8624   0.02258   0.01306  -0.0750   0.6779   1.0000
   5.000   0.8854   0.02197   0.01252  -0.0716   0.6412   1.0000
   5.250   0.9035   0.02163   0.01222  -0.0680   0.5920   1.0000
   5.500   0.9211   0.02166   0.01242  -0.0650   0.5392   1.0000
   5.750   0.9367   0.02179   0.01243  -0.0615   0.4532   1.0000
   6.000   0.9446   0.02314   0.01284  -0.0575   0.2933   1.0000
   6.250   0.9465   0.02609   0.01459  -0.0545   0.1524   1.0000
   6.500   0.9557   0.02849   0.01667  -0.0523   0.1144   1.0000
   6.750   0.9664   0.03063   0.01871  -0.0503   0.0915   1.0000
   7.000   0.9800   0.03256   0.02079  -0.0484   0.0737   1.0000
   7.250   0.9955   0.03470   0.02297  -0.0465   0.0626   1.0000
   7.500   1.0155   0.03674   0.02513  -0.0451   0.0529   1.0000
   7.750   1.0444   0.03934   0.02799  -0.0442   0.0470   1.0000
   8.000   1.0661   0.04169   0.03050  -0.0433   0.0412   1.0000
   8.250   1.0903   0.04512   0.03420  -0.0425   0.0386   1.0000
   8.500   1.1096   0.04863   0.03828  -0.0411   0.0370   1.0000
   8.750   1.1228   0.05205   0.04221  -0.0394   0.0349   1.0000
   9.000   1.1324   0.05519   0.04580  -0.0378   0.0328   1.0000
   9.250   1.1403   0.05844   0.04927  -0.0365   0.0313   1.0000
   9.500   1.1438   0.06248   0.05359  -0.0350   0.0305   1.0000
   9.750   1.1419   0.06660   0.05804  -0.0331   0.0304   1.0000
  10.000   1.1355   0.07057   0.06238  -0.0311   0.0303   1.0000
  10.250   1.1247   0.07445   0.06656  -0.0292   0.0303   1.0000
  10.500   1.1107   0.07822   0.07055  -0.0275   0.0303   1.0000
  10.750   1.0952   0.08225   0.07477  -0.0267   0.0304   1.0000
  11.250   1.0575   0.09174   0.08473  -0.0288   0.0308   1.0000
  11.500   1.0264   0.09926   0.09248  -0.0337   0.0316   1.0000
  11.750   0.9999   0.10831   0.10165  -0.0401   0.0325   1.0000
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