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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 50,000
Max Cl/Cd: 41.89 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe403-il-50000-n5.txt
Download as CSV file: xf-goe403-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3457   0.10486   0.09834  -0.0271   1.0000   0.0819
  -7.750  -0.3518   0.10366   0.09728  -0.0283   1.0000   0.0825
  -7.500  -0.3541   0.10192   0.09566  -0.0308   1.0000   0.0829
  -7.250  -0.3472   0.09722   0.09104  -0.0295   1.0000   0.0840
  -7.000  -0.3394   0.09318   0.08703  -0.0278   1.0000   0.0857
  -6.750  -0.3359   0.09022   0.08415  -0.0279   1.0000   0.0869
  -6.500  -0.3329   0.08731   0.08132  -0.0285   1.0000   0.0880
  -6.250  -0.3298   0.08450   0.07859  -0.0294   1.0000   0.0885
  -6.000  -0.3263   0.08156   0.07568  -0.0305   1.0000   0.0883
  -5.750  -0.3158   0.07616   0.07027  -0.0368   1.0000   0.0542
  -5.500  -0.3115   0.07291   0.06707  -0.0360   1.0000   0.0525
  -5.250  -0.3043   0.06964   0.06377  -0.0373   1.0000   0.0520
  -5.000  -0.2944   0.06621   0.06032  -0.0392   1.0000   0.0524
  -4.750  -0.2811   0.06252   0.05655  -0.0418   1.0000   0.0531
  -4.500  -0.2648   0.05858   0.05249  -0.0445   1.0000   0.0535
  -4.250  -0.2469   0.05454   0.04830  -0.0469   1.0000   0.0533
  -4.000  -0.2256   0.05031   0.04385  -0.0496   1.0000   0.0532
  -3.750  -0.1972   0.04540   0.03851  -0.0534   1.0000   0.0546
  -3.500  -0.1655   0.04266   0.03562  -0.0567   0.9945   0.0626
  -3.250  -0.1180   0.03735   0.02956  -0.0629   0.9879   0.0656
  -3.000  -0.0772   0.03458   0.02627  -0.0669   0.9800   0.0777
  -2.750  -0.0338   0.03092   0.02167  -0.0706   0.9728   0.0808
  -2.500   0.0079   0.02836   0.01843  -0.0735   0.9656   0.0854
  -2.250   0.0464   0.02703   0.01652  -0.0758   0.9561   0.0967
  -2.000   0.0831   0.02587   0.01516  -0.0779   0.9462   0.1053
  -1.750   0.1231   0.02455   0.01327  -0.0799   0.9375   0.1113
  -1.500   0.1622   0.02359   0.01210  -0.0819   0.9280   0.1196
  -1.250   0.2002   0.02277   0.01106  -0.0836   0.9174   0.1332
  -1.000   0.2390   0.02212   0.01031  -0.0857   0.9070   0.1632
  -0.750   0.2797   0.02139   0.00966  -0.0881   0.8975   0.2084
  -0.500   0.3156   0.02063   0.00918  -0.0897   0.8859   0.2790
  -0.250   0.3528   0.01832   0.00865  -0.0911   0.8748   1.0000
   0.000   0.3882   0.01837   0.00826  -0.0921   0.8615   1.0000
   0.250   0.4222   0.01843   0.00801  -0.0929   0.8479   1.0000
   0.500   0.4550   0.01849   0.00783  -0.0934   0.8337   1.0000
   0.750   0.4865   0.01858   0.00773  -0.0937   0.8192   1.0000
   1.000   0.5169   0.01868   0.00768  -0.0938   0.8043   1.0000
   1.250   0.5461   0.01881   0.00769  -0.0937   0.7890   1.0000
   1.500   0.5745   0.01896   0.00774  -0.0934   0.7737   1.0000
   1.750   0.6005   0.01917   0.00789  -0.0928   0.7571   1.0000
   2.000   0.6266   0.01939   0.00810  -0.0922   0.7406   1.0000
   2.250   0.6529   0.01961   0.00830  -0.0916   0.7247   1.0000
   2.500   0.6791   0.01984   0.00853  -0.0911   0.7093   1.0000
   2.750   0.7053   0.02008   0.00882  -0.0905   0.6944   1.0000
   3.000   0.7315   0.02034   0.00912  -0.0900   0.6800   1.0000
   3.250   0.7576   0.02061   0.00945  -0.0894   0.6660   1.0000
   3.500   0.7836   0.02091   0.00984  -0.0888   0.6524   1.0000
   3.750   0.8096   0.02123   0.01032  -0.0883   0.6391   1.0000
   4.000   0.8356   0.02158   0.01081  -0.0877   0.6264   1.0000
   4.250   0.8617   0.02194   0.01135  -0.0871   0.6139   1.0000
   4.500   0.8853   0.02193   0.01137  -0.0853   0.5886   1.0000
   4.750   0.9046   0.02197   0.01146  -0.0827   0.5526   1.0000
   5.000   0.9224   0.02210   0.01151  -0.0798   0.5094   1.0000
   5.250   0.9401   0.02244   0.01187  -0.0774   0.4676   1.0000
   5.500   0.9542   0.02291   0.01224  -0.0744   0.4049   1.0000
   5.750   0.9613   0.02418   0.01268  -0.0710   0.2504   1.0000
   6.000   0.9573   0.02827   0.01504  -0.0681   0.0492   1.0000
   6.250   0.9727   0.02990   0.01680  -0.0664   0.0407   1.0000
   6.500   0.9866   0.03158   0.01879  -0.0646   0.0371   1.0000
   6.750   0.9990   0.03325   0.02072  -0.0627   0.0350   1.0000
   7.000   1.0098   0.03496   0.02269  -0.0607   0.0327   1.0000
   7.250   1.0173   0.03685   0.02478  -0.0585   0.0305   1.0000
   7.500   1.0204   0.03901   0.02707  -0.0560   0.0290   1.0000
   7.750   1.0246   0.04096   0.02918  -0.0534   0.0283   1.0000
   8.000   1.0318   0.04287   0.03128  -0.0510   0.0279   1.0000
   8.250   1.0447   0.04472   0.03332  -0.0490   0.0276   1.0000
   8.500   1.0712   0.04658   0.03538  -0.0475   0.0272   1.0000
   8.750   1.1137   0.04907   0.03811  -0.0476   0.0267   1.0000
   9.000   1.1431   0.05192   0.04142  -0.0470   0.0258   1.0000
   9.250   1.1631   0.05498   0.04486  -0.0459   0.0250   1.0000
   9.500   1.1768   0.05822   0.04848  -0.0445   0.0247   1.0000
   9.750   1.1854   0.06163   0.05228  -0.0428   0.0248   1.0000
  10.000   1.1887   0.06510   0.05611  -0.0409   0.0251   1.0000
  10.250   1.1862   0.06851   0.05985  -0.0387   0.0254   1.0000
  10.500   1.1792   0.07200   0.06364  -0.0367   0.0256   1.0000
  10.750   1.1689   0.07562   0.06754  -0.0352   0.0259   1.0000
  11.000   1.1563   0.07957   0.07175  -0.0344   0.0261   1.0000
  11.250   1.1421   0.08385   0.07627  -0.0345   0.0263   1.0000
  11.500   1.1270   0.08852   0.08117  -0.0353   0.0265   1.0000
  11.750   1.1108   0.09367   0.08651  -0.0371   0.0266   1.0000
  12.000   1.0939   0.09934   0.09237  -0.0396   0.0268   1.0000
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