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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 50,000
Max Cl/Cd: 40.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe377-il-50000-n5.txt
Download as CSV file: xf-goe377-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 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  -0.3680   0.10102   0.09444  -0.0265   1.0000   0.0759
  -7.500  -0.3744   0.09967   0.09322  -0.0282   1.0000   0.0767
  -7.250  -0.3767   0.09802   0.09166  -0.0310   1.0000   0.0772
  -7.000  -0.3756   0.09553   0.08926  -0.0329   1.0000   0.0775
  -6.750  -0.3672   0.08975   0.08353  -0.0276   1.0000   0.0798
  -6.500  -0.3638   0.08662   0.08045  -0.0265   1.0000   0.0825
  -6.250  -0.3615   0.08400   0.07789  -0.0266   1.0000   0.0848
  -6.000  -0.3590   0.08152   0.07545  -0.0278   1.0000   0.0883
  -5.750  -0.3524   0.08030   0.07413  -0.0337   1.0000   0.0914
  -5.500  -0.3485   0.07600   0.06993  -0.0317   1.0000   0.0927
  -5.250  -0.3441   0.07260   0.06658  -0.0293   1.0000   0.0953
  -5.000  -0.3363   0.06989   0.06386  -0.0294   1.0000   0.1018
  -4.750  -0.3272   0.06682   0.06076  -0.0305   1.0000   0.1089
  -4.250  -0.3068   0.06100   0.05487  -0.0304   1.0000   0.1259
  -4.000  -0.2647   0.05468   0.04785  -0.0367   1.0000   0.0642
  -3.750  -0.2532   0.05140   0.04458  -0.0355   1.0000   0.0591
  -3.500  -0.2337   0.04794   0.04086  -0.0360   1.0000   0.0561
  -3.250  -0.2124   0.04469   0.03731  -0.0366   1.0000   0.0554
  -3.000  -0.1908   0.04197   0.03427  -0.0368   1.0000   0.0580
  -2.750  -0.1672   0.03916   0.03103  -0.0370   1.0000   0.0599
  -2.500  -0.1416   0.03638   0.02780  -0.0372   0.9994   0.0600
  -2.250  -0.1004   0.03347   0.02403  -0.0397   0.9934   0.0639
  -2.000  -0.0648   0.03142   0.02171  -0.0421   0.9871   0.0709
  -1.750  -0.0267   0.02931   0.01897  -0.0438   0.9805   0.0738
  -1.500   0.0099   0.02797   0.01727  -0.0458   0.9733   0.0846
  -1.250   0.0502   0.02664   0.01542  -0.0479   0.9670   0.0882
  -1.000   0.0865   0.02563   0.01394  -0.0491   0.9589   0.0907
  -0.750   0.1281   0.02475   0.01280  -0.0516   0.9524   0.0948
  -0.500   0.1653   0.02413   0.01198  -0.0533   0.9437   0.1015
  -0.250   0.2015   0.02362   0.01134  -0.0550   0.9346   0.1130
   0.000   0.2418   0.02313   0.01090  -0.0577   0.9266   0.1430
   0.250   0.2759   0.02249   0.01054  -0.0591   0.9159   0.2012
   0.500   0.3306   0.02047   0.01013  -0.0644   0.9096   1.0000
   0.750   0.3720   0.02057   0.00992  -0.0669   0.8988   1.0000
   1.000   0.4099   0.02060   0.00975  -0.0686   0.8853   1.0000
   1.250   0.4481   0.02057   0.00955  -0.0702   0.8710   1.0000
   1.500   0.4806   0.02054   0.00943  -0.0707   0.8546   1.0000
   1.750   0.5121   0.02051   0.00933  -0.0709   0.8379   1.0000
   2.000   0.5437   0.02045   0.00923  -0.0711   0.8214   1.0000
   2.250   0.5751   0.02038   0.00914  -0.0712   0.8049   1.0000
   2.500   0.6067   0.02029   0.00906  -0.0712   0.7881   1.0000
   2.750   0.6344   0.02028   0.00906  -0.0706   0.7691   1.0000
   3.000   0.6627   0.02026   0.00906  -0.0701   0.7494   1.0000
   3.250   0.6930   0.02019   0.00904  -0.0698   0.7302   1.0000
   3.500   0.7190   0.02027   0.00916  -0.0688   0.7077   1.0000
   3.750   0.7477   0.02028   0.00919  -0.0682   0.6861   1.0000
   4.000   0.7734   0.02043   0.00939  -0.0673   0.6615   1.0000
   4.250   0.7990   0.02060   0.00965  -0.0663   0.6364   1.0000
   4.500   0.8245   0.02083   0.00990  -0.0653   0.6110   1.0000
   4.750   0.8495   0.02111   0.01021  -0.0642   0.5850   1.0000
   5.000   0.8737   0.02149   0.01066  -0.0631   0.5589   1.0000
   5.250   0.8969   0.02194   0.01117  -0.0619   0.5325   1.0000
   5.500   0.9199   0.02245   0.01176  -0.0608   0.5071   1.0000
   5.750   0.9426   0.02301   0.01238  -0.0596   0.4825   1.0000
   6.000   0.9647   0.02359   0.01306  -0.0584   0.4585   1.0000
   6.250   0.9860   0.02422   0.01390  -0.0571   0.4347   1.0000
   6.500   1.0081   0.02487   0.01466  -0.0559   0.4139   1.0000
   6.750   1.0295   0.02558   0.01562  -0.0546   0.3937   1.0000
   7.000   1.0478   0.02623   0.01639  -0.0528   0.3689   1.0000
   7.250   1.0550   0.02683   0.01690  -0.0493   0.3246   1.0000
   7.500   1.0618   0.02764   0.01764  -0.0461   0.2770   1.0000
   7.750   1.0654   0.02880   0.01864  -0.0428   0.2038   1.0000
   8.000   1.0653   0.03124   0.02025  -0.0397   0.0915   1.0000
   8.250   1.0670   0.03416   0.02271  -0.0369   0.0579   1.0000
   8.500   1.0703   0.03657   0.02515  -0.0341   0.0499   1.0000
   8.750   1.0734   0.03868   0.02745  -0.0312   0.0440   1.0000
   9.000   1.0730   0.04101   0.02986  -0.0283   0.0401   1.0000
   9.250   1.0770   0.04304   0.03216  -0.0258   0.0369   1.0000
   9.500   1.0795   0.04533   0.03463  -0.0235   0.0348   1.0000
   9.750   1.0825   0.04772   0.03716  -0.0214   0.0333   1.0000
  10.000   1.0881   0.05027   0.03980  -0.0196   0.0321   1.0000
  10.250   1.0998   0.05270   0.04259  -0.0178   0.0305   1.0000
  10.500   1.1088   0.05536   0.04557  -0.0163   0.0287   1.0000
  10.750   1.1138   0.05824   0.04871  -0.0150   0.0272   1.0000
  11.000   1.1171   0.06138   0.05210  -0.0138   0.0262   1.0000
  11.250   1.1185   0.06484   0.05584  -0.0128   0.0258   1.0000
  11.500   1.1159   0.06864   0.05992  -0.0121   0.0255   1.0000
  11.750   1.1097   0.07274   0.06430  -0.0119   0.0254   1.0000
  12.000   1.1001   0.07729   0.06910  -0.0124   0.0253   1.0000
  12.250   1.0880   0.08223   0.07432  -0.0136   0.0254   1.0000
  12.500   1.0731   0.08793   0.08026  -0.0157   0.0255   1.0000
  12.750   1.0567   0.09422   0.08678  -0.0189   0.0257   1.0000
  13.000   1.0388   0.10136   0.09413  -0.0229   0.0260   1.0000
  13.250   1.0188   0.10972   0.10268  -0.0281   0.0264   1.0000
  13.500   0.9990   0.11893   0.11205  -0.0340   0.0269   1.0000
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