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GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 780 AIRFOIL (goe780-il)
Reynolds number: 50,000
Max Cl/Cd: 19.49 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe780-il-50000-n5.txt
Download as CSV file: xf-goe780-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 780 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4764   0.10772   0.10099  -0.0483   1.0000   0.0474
 -10.500  -0.4796   0.10291   0.09627  -0.0500   1.0000   0.0444
 -10.000  -0.5006   0.09180   0.08528  -0.0583   1.0000   0.0388
  -9.750  -0.5062   0.08795   0.08148  -0.0584   1.0000   0.0379
  -9.500  -0.5164   0.08441   0.07798  -0.0583   1.0000   0.0373
  -9.250  -0.5291   0.08145   0.07504  -0.0573   1.0000   0.0367
  -9.000  -0.5481   0.07863   0.07226  -0.0548   1.0000   0.0362
  -8.750  -0.5686   0.07673   0.07042  -0.0507   1.0000   0.0359
  -8.500  -0.5925   0.07550   0.06924  -0.0452   1.0000   0.0356
  -8.250  -0.6167   0.07425   0.06801  -0.0393   1.0000   0.0354
  -8.000  -0.6386   0.07296   0.06669  -0.0336   1.0000   0.0350
  -7.750  -0.6587   0.07131   0.06498  -0.0280   1.0000   0.0346
  -7.500  -0.6760   0.06937   0.06294  -0.0227   1.0000   0.0343
  -7.250  -0.6789   0.06597   0.05925  -0.0204   0.9954   0.0332
  -7.000  -0.6765   0.06168   0.05450  -0.0185   0.9883   0.0320
  -6.500  -0.6606   0.05496   0.04666  -0.0141   0.9760   0.0303
  -6.250  -0.6509   0.05167   0.04295  -0.0118   0.9705   0.0302
  -5.750  -0.6242   0.04586   0.03653  -0.0087   0.9610   0.0332
  -5.500  -0.6054   0.04335   0.03347  -0.0074   0.9568   0.0346
  -5.250  -0.5797   0.04054   0.03008  -0.0067   0.9538   0.0359
  -5.000  -0.5569   0.03824   0.02729  -0.0054   0.9500   0.0368
  -4.750  -0.5241   0.03597   0.02442  -0.0055   0.9471   0.0392
  -4.500  -0.4829   0.03347   0.02176  -0.0080   0.9457   0.0473
  -4.250  -0.4303   0.03120   0.01923  -0.0121   0.9457   0.0585
  -4.000  -0.3982   0.02974   0.01753  -0.0130   0.9433   0.0742
  -3.750  -0.3019   0.02606   0.01752  -0.0224   0.9517   0.7988
  -3.500  -0.1750   0.02968   0.01992  -0.0350   0.9603   0.9537
  -3.250  -0.1006   0.02943   0.01905  -0.0449   0.9616   0.9796
  -3.000  -0.0540   0.02900   0.01819  -0.0501   0.9593   0.9900
  -2.750  -0.0114   0.02860   0.01749  -0.0547   0.9569   0.9977
  -2.500   0.0217   0.02837   0.01702  -0.0573   0.9538   1.0000
  -2.250   0.0397   0.02829   0.01675  -0.0568   0.9475   1.0000
  -2.000   0.0646   0.02820   0.01651  -0.0576   0.9429   1.0000
  -1.750   0.0902   0.02814   0.01632  -0.0585   0.9389   1.0000
  -1.500   0.1066   0.02818   0.01626  -0.0575   0.9330   1.0000
  -1.250   0.1312   0.02819   0.01617  -0.0582   0.9288   1.0000
  -1.000   0.1535   0.02825   0.01616  -0.0583   0.9246   1.0000
  -0.750   0.1687   0.02840   0.01627  -0.0570   0.9190   1.0000
  -0.500   0.1927   0.02849   0.01633  -0.0574   0.9151   1.0000
  -0.250   0.2132   0.02865   0.01648  -0.0571   0.9109   1.0000
   0.000   0.2256   0.02890   0.01674  -0.0552   0.9053   1.0000
   0.250   0.2486   0.02908   0.01695  -0.0552   0.9015   1.0000
   0.500   0.2724   0.02928   0.01722  -0.0555   0.8980   1.0000
   0.750   0.2789   0.02967   0.01765  -0.0524   0.8918   1.0000
   1.000   0.2997   0.02994   0.01801  -0.0519   0.8879   1.0000
   1.250   0.3263   0.03018   0.01837  -0.0526   0.8850   1.0000
   1.500   0.3273   0.03069   0.01894  -0.0484   0.8783   1.0000
   1.750   0.3468   0.03104   0.01948  -0.0477   0.8743   1.0000
   2.000   0.3721   0.03137   0.02001  -0.0481   0.8714   1.0000
   2.250   0.3714   0.03195   0.02067  -0.0436   0.8644   1.0000
   2.500   0.3906   0.03237   0.02132  -0.0428   0.8605   1.0000
   2.750   0.4108   0.03283   0.02207  -0.0421   0.8570   1.0000
   3.000   0.4128   0.03344   0.02284  -0.0382   0.8503   1.0000
   3.250   0.4502   0.03360   0.02345  -0.0402   0.8445   1.0000
   3.500   0.5329   0.02734   0.01422  -0.0326   0.0791   1.0000
   3.750   0.5356   0.02848   0.01541  -0.0282   0.0615   1.0000
   4.000   0.5397   0.02945   0.01645  -0.0242   0.0521   1.0000
   4.250   0.5439   0.03039   0.01752  -0.0202   0.0460   1.0000
   4.500   0.5465   0.03151   0.01868  -0.0159   0.0433   1.0000
   4.750   0.5538   0.03257   0.01996  -0.0121   0.0410   1.0000
   5.000   0.5703   0.03359   0.02116  -0.0097   0.0378   1.0000
   5.250   0.6415   0.03543   0.02332  -0.0151   0.0324   1.0000
   5.500   0.7046   0.03819   0.02645  -0.0193   0.0316   1.0000
   5.750   0.7365   0.04081   0.02944  -0.0190   0.0315   1.0000
   6.000   0.7594   0.04330   0.03232  -0.0175   0.0311   1.0000
   6.250   0.7765   0.04577   0.03518  -0.0152   0.0307   1.0000
   6.500   0.7894   0.04839   0.03820  -0.0124   0.0301   1.0000
   6.750   0.7991   0.05093   0.04110  -0.0093   0.0300   1.0000
   7.000   0.8055   0.05362   0.04416  -0.0057   0.0299   1.0000
   7.250   0.8093   0.05648   0.04736  -0.0020   0.0306   1.0000
   7.500   0.8105   0.05934   0.05052   0.0019   0.0313   1.0000
   7.750   0.8099   0.06215   0.05358   0.0057   0.0320   1.0000
   8.000   0.8070   0.06506   0.05680   0.0096   0.0327   1.0000
   8.250   0.8034   0.06804   0.05995   0.0133   0.0334   1.0000
   8.500   0.8045   0.07193   0.06386   0.0157   0.0343   1.0000
   8.750   0.7852   0.07322   0.06563   0.0223   0.0361   1.0000
   9.000   0.7676   0.07599   0.06859   0.0273   0.0374   1.0000
   9.250   0.7498   0.07839   0.07109   0.0319   0.0381   1.0000
   9.500   0.7309   0.08065   0.07343   0.0362   0.0387   1.0000
   9.750   0.7106   0.08350   0.07634   0.0396   0.0392   1.0000
  10.000   0.6930   0.08661   0.07951   0.0418   0.0400   1.0000
  10.250   0.6762   0.09012   0.08305   0.0431   0.0405   1.0000
  10.500   0.6630   0.09406   0.08700   0.0438   0.0414   1.0000
  10.750   0.6594   0.09793   0.09093   0.0442   0.0446   1.0000
  11.000   0.6336   0.10294   0.09597   0.0422   0.0457   1.0000
  11.250   0.6163   0.10879   0.10169   0.0390   0.0471   1.0000
  11.500   0.6069   0.11466   0.10750   0.0358   0.0491   1.0000
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