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GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 383 AIRFOIL (goe383-il)
Reynolds number: 50,000
Max Cl/Cd: 13.94 at α=0.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe383-il-50000-n5.txt
Download as CSV file: xf-goe383-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 383 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1408   0.10891   0.10140  -0.0837   0.9392   0.0856
 -10.750  -0.1376   0.10403   0.09651  -0.0873   0.9287   0.0850
 -10.500  -0.1349   0.09864   0.09110  -0.0916   0.9204   0.0848
 -10.000  -0.2294   0.07470   0.06687  -0.1091   0.8936   0.0815
  -9.750  -0.2592   0.06886   0.06083  -0.1121   0.8809   0.0811
  -9.500  -0.2888   0.06502   0.05677  -0.1112   0.8672   0.0809
  -9.250  -0.3128   0.06189   0.05339  -0.1092   0.8548   0.0809
  -9.000  -0.3265   0.05851   0.04964  -0.1077   0.8462   0.0810
  -8.750  -0.3379   0.05605   0.04686  -0.1051   0.8358   0.0812
  -8.500  -0.3394   0.05345   0.04389  -0.1032   0.8277   0.0815
  -8.250  -0.3233   0.05132   0.04155  -0.1029   0.8228   0.0821
  -8.000  -0.3210   0.05017   0.04025  -0.1003   0.8127   0.0825
  -7.750  -0.3065   0.04851   0.03839  -0.0993   0.8064   0.0832
  -7.500  -0.2863   0.04670   0.03633  -0.0990   0.8020   0.0842
  -7.250  -0.2796   0.04580   0.03527  -0.0966   0.7932   0.0852
  -7.000  -0.2641   0.04452   0.03372  -0.0953   0.7865   0.0868
  -6.750  -0.2417   0.04293   0.03177  -0.0948   0.7819   0.0889
  -6.500  -0.2217   0.04219   0.03102  -0.0940   0.7760   0.0907
  -6.250  -0.2090   0.04168   0.03043  -0.0920   0.7676   0.0925
  -6.000  -0.1836   0.04057   0.02913  -0.0916   0.7622   0.0948
  -5.750  -0.1522   0.03931   0.02766  -0.0919   0.7583   0.0974
  -5.500  -0.1425   0.03918   0.02756  -0.0894   0.7489   0.0992
  -5.250  -0.1195   0.03853   0.02683  -0.0886   0.7425   0.1029
  -5.000  -0.0892   0.03762   0.02584  -0.0887   0.7380   0.1078
  -4.750  -0.0711   0.03730   0.02548  -0.0872   0.7310   0.1126
  -4.500  -0.0555   0.03706   0.02522  -0.0854   0.7232   0.1175
  -4.250  -0.0280   0.03637   0.02444  -0.0851   0.7182   0.1259
  -4.000   0.0030   0.03547   0.02356  -0.0852   0.7146   0.1389
  -3.750   0.0068   0.03576   0.02393  -0.0821   0.7048   0.1492
  -3.500   0.0281   0.03513   0.02346  -0.0812   0.6988   0.1718
  -3.250   0.0559   0.03422   0.02279  -0.0812   0.6947   0.2131
  -3.000   0.0710   0.03410   0.02290  -0.0796   0.6879   0.2584
  -2.750   0.0812   0.03424   0.02322  -0.0772   0.6795   0.3032
  -2.500   0.1046   0.03364   0.02293  -0.0764   0.6747   0.3723
  -2.250   0.1301   0.03285   0.02266  -0.0752   0.6713   0.4697
  -2.000   0.1273   0.03370   0.02387  -0.0709   0.6606   0.5295
  -1.750   0.1456   0.03366   0.02419  -0.0681   0.6547   0.6155
  -1.500   0.1732   0.03346   0.02406  -0.0664   0.6509   0.6905
  -1.250   0.1879   0.03397   0.02461  -0.0636   0.6440   0.7395
  -1.000   0.1978   0.03482   0.02553  -0.0606   0.6350   0.7816
  -0.750   0.2332   0.03489   0.02553  -0.0603   0.6306   0.8319
  -0.500   0.2854   0.03483   0.02530  -0.0625   0.6276   0.8847
  -0.250   0.3163   0.03617   0.02658  -0.0640   0.6180   0.9221
   0.000   0.3712   0.03665   0.02688  -0.0690   0.6118   0.9504
   0.250   0.4370   0.03653   0.02651  -0.0756   0.6079   0.9689
   0.500   0.5037   0.03614   0.02586  -0.0822   0.6049   0.9848
   1.000   0.5053   0.03836   0.02799  -0.0774   0.5872   1.0000
   1.250   0.5255   0.03818   0.02763  -0.0761   0.5836   1.0000
   1.750   0.4718   0.04145   0.03079  -0.0626   0.5650   1.0000
   2.000   0.5018   0.04126   0.03042  -0.0625   0.5622   1.0000
   2.500   0.4753   0.04527   0.03430  -0.0544   0.5439   1.0000
   2.750   0.4764   0.04712   0.03607  -0.0524   0.5367   1.0000
   4.250   0.5544   0.05452   0.04299  -0.0468   0.5028   1.0000
   4.750   0.5557   0.05941   0.04784  -0.0446   0.4871   1.0000
   5.250   0.5599   0.06421   0.05259  -0.0428   0.4720   1.0000
   5.500   0.5886   0.06425   0.05257  -0.0426   0.4691   1.0000
   6.000   0.5937   0.06909   0.05737  -0.0411   0.4538   1.0000
   6.250   0.6233   0.06900   0.05723  -0.0408   0.4510   1.0000
   6.750   0.6279   0.07401   0.06223  -0.0395   0.4353   1.0000
   7.000   0.6579   0.07382   0.06198  -0.0392   0.4325   1.0000
   7.500   0.6600   0.07924   0.06743  -0.0381   0.4165   1.0000
   7.750   0.6899   0.07902   0.06717  -0.0377   0.4139   1.0000
   8.250   0.6889   0.08499   0.07318  -0.0369   0.3975   1.0000
   8.500   0.7180   0.08481   0.07298  -0.0365   0.3950   1.0000
   8.750   0.6916   0.09076   0.07900  -0.0363   0.3822   1.0000
   9.000   0.7140   0.09134   0.07956  -0.0360   0.3786   1.0000
   9.250   0.7422   0.09123   0.07943  -0.0356   0.3763   1.0000
   9.500   0.7135   0.09770   0.08599  -0.0358   0.3634   1.0000
   9.750   0.7350   0.09840   0.08668  -0.0355   0.3601   1.0000
  10.000   0.7618   0.09847   0.08674  -0.0351   0.3580   1.0000
  10.250   0.7313   0.10546   0.09381  -0.0358   0.3456   1.0000
  10.500   0.7517   0.10628   0.09463  -0.0355   0.3424   1.0000
  10.750   0.7750   0.10678   0.09513  -0.0352   0.3402   1.0000
  11.000   0.7441   0.11425   0.10269  -0.0365   0.3292   1.0000
  11.250   0.7616   0.11549   0.10395  -0.0364   0.3261   1.0000
  11.500   0.7843   0.11606   0.10452  -0.0361   0.3239   1.0000
  11.750   0.7558   0.12344   0.11199  -0.0378   0.3146   1.0000
  12.000   0.7669   0.12568   0.11426  -0.0381   0.3114   1.0000
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