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GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 514 AIRFOIL (goe514-il)
Reynolds number: 50,000
Max Cl/Cd: 26.06 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe514-il-50000-n5.txt
Download as CSV file: xf-goe514-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 514 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3053   0.11881   0.11263  -0.0462   0.9848   0.0629
  -9.750  -0.3058   0.11375   0.10760  -0.0496   0.9792   0.0632
  -9.500  -0.3119   0.10750   0.10138  -0.0544   0.9736   0.0638
  -9.250  -0.2996   0.10561   0.09951  -0.0553   0.9675   0.0659
  -9.000  -0.2936   0.10225   0.09615  -0.0579   0.9617   0.0682
  -8.750  -0.3022   0.09764   0.09158  -0.0605   0.9540   0.0692
  -8.500  -0.3159   0.09201   0.08599  -0.0647   0.9466   0.0699
  -8.250  -0.3408   0.08762   0.08164  -0.0646   0.9361   0.0700
  -8.000  -0.3615   0.08143   0.07541  -0.0663   0.9274   0.0707
  -7.750  -0.3884   0.07390   0.06775  -0.0671   0.9172   0.0714
  -7.500  -0.4288   0.06352   0.05692  -0.0666   0.9067   0.0727
  -7.250  -0.4347   0.05797   0.05095  -0.0658   0.8995   0.0758
  -7.000  -0.4211   0.05742   0.05040  -0.0642   0.8921   0.0793
  -6.750  -0.4267   0.05209   0.04437  -0.0621   0.8844   0.0846
  -6.500  -0.3991   0.05223   0.04463  -0.0623   0.8792   0.0906
  -6.250  -0.4015   0.04892   0.04073  -0.0589   0.8700   0.0974
  -6.000  -0.3663   0.05006   0.04209  -0.0599   0.8643   0.1051
  -5.750  -0.3553   0.04906   0.04090  -0.0575   0.8536   0.1125
  -5.500  -0.3245   0.04754   0.03903  -0.0583   0.8472   0.1238
  -5.250  -0.3101   0.04709   0.03846  -0.0560   0.8352   0.1316
  -5.000  -0.2882   0.04613   0.03729  -0.0550   0.8260   0.1402
  -4.750  -0.2665   0.04431   0.03494  -0.0542   0.8177   0.1518
  -4.500  -0.2464   0.04437   0.03510  -0.0527   0.8078   0.1578
  -4.250  -0.2194   0.04280   0.03308  -0.0525   0.8010   0.1698
  -4.000  -0.2019   0.04278   0.03309  -0.0506   0.7905   0.1761
  -3.750  -0.1707   0.04160   0.03159  -0.0509   0.7843   0.1884
  -3.500  -0.1543   0.04143   0.03136  -0.0488   0.7733   0.1957
  -3.250  -0.1193   0.04058   0.03029  -0.0495   0.7674   0.2081
  -3.000  -0.1033   0.04012   0.02955  -0.0475   0.7558   0.2189
  -2.750  -0.0657   0.03946   0.02880  -0.0484   0.7505   0.2295
  -2.500  -0.0501   0.03931   0.02851  -0.0463   0.7380   0.2381
  -2.250  -0.0234   0.03881   0.02775  -0.0457   0.7291   0.2491
  -2.000   0.0043   0.03840   0.02730  -0.0452   0.7202   0.2586
  -1.750   0.0271   0.03813   0.02689  -0.0441   0.7099   0.2700
  -1.500   0.0594   0.03747   0.02601  -0.0442   0.7023   0.2830
  -1.250   0.0821   0.03718   0.02569  -0.0431   0.6910   0.2908
  -1.000   0.1215   0.03625   0.02446  -0.0444   0.6841   0.2989
  -0.750   0.1477   0.03595   0.02409  -0.0440   0.6721   0.3041
  -0.500   0.1937   0.03499   0.02290  -0.0464   0.6655   0.3140
  -0.250   0.2215   0.03486   0.02267  -0.0465   0.6526   0.3209
   0.000   0.2746   0.03383   0.02142  -0.0501   0.6465   0.3310
   0.250   0.2997   0.03381   0.02132  -0.0497   0.6326   0.3378
   0.500   0.3318   0.03354   0.02095  -0.0503   0.6212   0.3471
   0.750   0.3746   0.03284   0.02014  -0.0524   0.6126   0.3596
   1.000   0.3973   0.03292   0.02014  -0.0516   0.5997   0.3703
   1.250   0.4334   0.03246   0.01958  -0.0527   0.5904   0.3835
   1.500   0.4606   0.03228   0.01938  -0.0525   0.5795   0.3950
   1.750   0.4828   0.03230   0.01937  -0.0516   0.5685   0.4076
   2.000   0.5168   0.03181   0.01882  -0.0523   0.5604   0.4253
   2.250   0.5310   0.03206   0.01912  -0.0503   0.5496   0.4417
   2.500   0.5648   0.03137   0.01849  -0.0510   0.5425   0.4728
   3.000   0.7553   0.03157   0.01969  -0.0776   0.5191   1.0000
   3.250   0.7775   0.03187   0.01981  -0.0766   0.5115   1.0000
   3.500   0.7963   0.03230   0.02010  -0.0752   0.5044   1.0000
   3.750   0.8104   0.03286   0.02056  -0.0731   0.4971   1.0000
   4.000   0.8451   0.03291   0.02039  -0.0741   0.4915   1.0000
   4.250   0.8455   0.03389   0.02138  -0.0700   0.4843   1.0000
   4.500   0.8656   0.03436   0.02175  -0.0689   0.4786   1.0000
   4.750   0.8994   0.03451   0.02172  -0.0699   0.4738   1.0000
   5.000   0.8949   0.03570   0.02298  -0.0652   0.4672   1.0000
   5.250   0.9124   0.03630   0.02351  -0.0638   0.4619   1.0000
   5.500   0.9469   0.03644   0.02351  -0.0648   0.4576   1.0000
   5.750   0.9409   0.03783   0.02497  -0.0602   0.4521   1.0000
   6.000   0.9459   0.03895   0.02611  -0.0572   0.4471   1.0000
   6.250   0.9685   0.03948   0.02659  -0.0566   0.4429   1.0000
   6.500   1.0064   0.03957   0.02655  -0.0582   0.4394   1.0000
   6.750   0.9726   0.04217   0.02935  -0.0504   0.4334   1.0000
   7.000   0.9735   0.04366   0.03088  -0.0473   0.4285   1.0000
   7.250   0.9974   0.04416   0.03135  -0.0469   0.4249   1.0000
   7.500   1.0359   0.04414   0.03124  -0.0483   0.4221   1.0000
   7.750   0.9505   0.05041   0.03782  -0.0370   0.4144   1.0000
   8.000   0.9417   0.05305   0.04053  -0.0340   0.4093   1.0000
   8.250   0.9686   0.05326   0.04071  -0.0338   0.4064   1.0000
   8.500   1.0118   0.05249   0.03988  -0.0349   0.4044   1.0000
   9.000   0.7687   0.08178   0.06972  -0.0244   0.3745   1.0000
   9.250   0.7850   0.08279   0.07072  -0.0237   0.3715   1.0000
   9.500   0.8085   0.08291   0.07084  -0.0229   0.3697   1.0000
  10.000   0.7568   0.09582   0.08388  -0.0227   0.3547   1.0000
  10.250   0.7784   0.09626   0.08433  -0.0219   0.3523   1.0000
  10.750   0.7432   0.10700   0.09519  -0.0222   0.3394   1.0000
  11.000   0.7605   0.10806   0.09627  -0.0217   0.3364   1.0000
  11.250   0.7846   0.10823   0.09646  -0.0209   0.3343   1.0000
  11.500   0.7446   0.11629   0.10459  -0.0220   0.3246   1.0000
  11.750   0.7584   0.11770   0.10604  -0.0216   0.3207   1.0000
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