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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 500,000
Max Cl/Cd: 96.02 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe376-il-500000-n5.txt
Download as CSV file: xf-goe376-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3132   0.09273   0.09058  -0.0209   1.0000   0.0089
  -7.750  -0.3144   0.09032   0.08820  -0.0204   1.0000   0.0089
  -7.500  -0.3135   0.08772   0.08564  -0.0208   0.9993   0.0088
  -7.250  -0.2942   0.08333   0.08125  -0.0268   0.9935   0.0088
  -6.750  -0.2540   0.07399   0.07190  -0.0392   0.9749   0.0092
  -6.500  -0.2339   0.07022   0.06811  -0.0441   0.9601   0.0099
  -6.250  -0.2047   0.06656   0.06442  -0.0503   0.9469   0.0104
  -6.000  -0.1642   0.06170   0.05948  -0.0600   0.9361   0.0115
  -5.750  -0.1110   0.05358   0.05119  -0.0749   0.9237   0.0124
  -5.500  -0.0697   0.05082   0.04831  -0.0816   0.9089   0.0129
  -5.250  -0.0352   0.04782   0.04517  -0.0869   0.8904   0.0144
  -5.000  -0.0073   0.04395   0.04113  -0.0907   0.8718   0.0150
  -4.750   0.0198   0.03968   0.03662  -0.0938   0.8539   0.0159
  -4.500   0.0414   0.03812   0.03495  -0.0943   0.8360   0.0164
  -4.250   0.0643   0.03624   0.03292  -0.0949   0.8173   0.0173
  -3.750   0.1161   0.03008   0.02620  -0.0961   0.7802   0.0200
  -3.500   0.1366   0.02918   0.02520  -0.0958   0.7635   0.0207
  -3.250   0.1670   0.02800   0.02372  -0.0954   0.7492   0.0242
  -3.000   0.1913   0.02589   0.02134  -0.0948   0.7358   0.0243
  -2.750   0.2149   0.02400   0.01918  -0.0941   0.7226   0.0243
  -2.500   0.2388   0.02237   0.01727  -0.0934   0.7100   0.0244
  -2.250   0.2597   0.01980   0.01448  -0.0928   0.6986   0.0251
  -2.000   0.2827   0.01895   0.01356  -0.0924   0.6865   0.0258
  -1.750   0.3068   0.01807   0.01253  -0.0919   0.6738   0.0266
  -1.500   0.3315   0.01703   0.01128  -0.0911   0.6604   0.0273
  -1.250   0.3562   0.01609   0.01011  -0.0902   0.6440   0.0282
  -1.000   0.3806   0.01520   0.00896  -0.0892   0.6241   0.0286
  -0.750   0.4048   0.01438   0.00788  -0.0882   0.5991   0.0282
  -0.500   0.4290   0.01376   0.00701  -0.0872   0.5732   0.0283
  -0.250   0.4537   0.01341   0.00644  -0.0863   0.5489   0.0293
   0.250   0.5030   0.01220   0.00482  -0.0846   0.5059   0.0270
   0.500   0.5280   0.01182   0.00426  -0.0839   0.4883   0.0265
   1.000   0.5782   0.01128   0.00351  -0.0825   0.4596   0.0268
   1.250   0.6033   0.01109   0.00325  -0.0819   0.4471   0.0272
   1.500   0.6284   0.01094   0.00305  -0.0813   0.4363   0.0276
   1.750   0.6535   0.01084   0.00289  -0.0806   0.4272   0.0281
   2.000   0.6788   0.01073   0.00277  -0.0800   0.4187   0.0284
   2.250   0.7040   0.01074   0.00275  -0.0795   0.4099   0.0298
   2.500   0.7289   0.01073   0.00270  -0.0789   0.3987   0.0302
   2.750   0.7539   0.01068   0.00264  -0.0782   0.3876   0.0302
   3.000   0.7787   0.01068   0.00260  -0.0776   0.3753   0.0301
   3.250   0.8036   0.01070   0.00260  -0.0770   0.3639   0.0302
   3.500   0.8287   0.01075   0.00263  -0.0764   0.3535   0.0303
   3.750   0.8538   0.01080   0.00267  -0.0759   0.3420   0.0307
   4.000   0.8786   0.01089   0.00273  -0.0753   0.3287   0.0313
   4.250   0.9032   0.01101   0.00278  -0.0747   0.3137   0.0326
   4.500   0.9277   0.01117   0.00289  -0.0740   0.2984   0.0342
   4.750   0.9519   0.01136   0.00303  -0.0734   0.2835   0.0368
   5.000   0.9761   0.01156   0.00319  -0.0727   0.2701   0.0398
   5.250   0.9997   0.01182   0.00341  -0.0720   0.2537   0.0439
   5.750   1.0841   0.01129   0.00431  -0.0798   0.2093   1.0000
   6.000   1.1063   0.01166   0.00461  -0.0788   0.1921   1.0000
   6.250   1.1285   0.01203   0.00489  -0.0779   0.1758   1.0000
   6.500   1.1500   0.01246   0.00521  -0.0769   0.1529   1.0000
   6.750   1.1701   0.01300   0.00560  -0.0756   0.1269   1.0000
   7.000   1.1884   0.01370   0.00612  -0.0741   0.0959   1.0000
   7.250   1.1972   0.01529   0.00724  -0.0712   0.0220   1.0000
   7.500   1.2168   0.01586   0.00780  -0.0698   0.0150   1.0000
   7.750   1.2376   0.01629   0.00831  -0.0687   0.0134   1.0000
   8.000   1.2576   0.01680   0.00889  -0.0674   0.0120   1.0000
   8.250   1.2761   0.01742   0.00961  -0.0658   0.0105   1.0000
   8.500   1.2946   0.01801   0.01029  -0.0643   0.0096   1.0000
   8.750   1.3133   0.01855   0.01091  -0.0629   0.0089   1.0000
   9.000   1.3307   0.01918   0.01162  -0.0613   0.0084   1.0000
   9.250   1.3471   0.01985   0.01237  -0.0596   0.0079   1.0000
   9.500   1.3618   0.02060   0.01321  -0.0576   0.0074   1.0000
   9.750   1.3731   0.02155   0.01425  -0.0552   0.0070   1.0000
  10.000   1.3785   0.02266   0.01546  -0.0517   0.0066   1.0000
  10.250   1.3901   0.02333   0.01622  -0.0493   0.0064   1.0000
  10.500   1.3992   0.02418   0.01716  -0.0467   0.0061   1.0000
  10.750   1.4061   0.02520   0.01827  -0.0439   0.0058   1.0000
  11.000   1.4107   0.02641   0.01961  -0.0411   0.0056   1.0000
  11.250   1.4179   0.02751   0.02079  -0.0389   0.0054   1.0000
  11.500   1.4191   0.02911   0.02251  -0.0364   0.0053   1.0000
  11.750   1.4231   0.03063   0.02411  -0.0345   0.0051   1.0000
  12.000   1.4247   0.03245   0.02604  -0.0327   0.0050   1.0000
  12.250   1.4232   0.03471   0.02842  -0.0311   0.0049   1.0000
  12.500   1.4231   0.03702   0.03083  -0.0301   0.0047   1.0000
  12.750   1.4202   0.03980   0.03373  -0.0293   0.0047   1.0000
  13.000   1.4145   0.04309   0.03715  -0.0289   0.0046   1.0000
  13.250   1.4088   0.04656   0.04074  -0.0289   0.0046   1.0000
  13.500   1.3947   0.05124   0.04556  -0.0292   0.0044   1.0000
  13.750   1.3903   0.05487   0.04931  -0.0297   0.0044   1.0000
  14.000   1.3840   0.05887   0.05344  -0.0303   0.0044   1.0000
  14.250   1.3774   0.06303   0.05773  -0.0312   0.0043   1.0000
  14.500   1.3707   0.06731   0.06213  -0.0322   0.0043   1.0000
  14.750   1.3630   0.07183   0.06678  -0.0333   0.0043   1.0000
  15.000   1.3563   0.07631   0.07138  -0.0346   0.0042   1.0000
  15.250   1.3486   0.08104   0.07623  -0.0360   0.0041   1.0000
  15.500   1.3408   0.08581   0.08112  -0.0374   0.0041   1.0000
  15.750   1.3331   0.09072   0.08615  -0.0390   0.0040   1.0000
  16.000   1.3263   0.09560   0.09116  -0.0408   0.0039   1.0000
  16.250   1.3186   0.10066   0.09634  -0.0426   0.0038   1.0000
  16.500   1.3105   0.10579   0.10158  -0.0444   0.0039   1.0000
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