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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 200,000
Max Cl/Cd: 72.98 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe403-il-200000-n5.txt
Download as CSV file: xf-goe403-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3354   0.08996   0.08667  -0.0269   1.0000   0.0133
  -7.500  -0.3431   0.08642   0.08323  -0.0280   1.0000   0.0116
  -7.250  -0.3442   0.08423   0.08111  -0.0275   1.0000   0.0114
  -7.000  -0.3415   0.08179   0.07873  -0.0280   1.0000   0.0113
  -6.750  -0.3434   0.07869   0.07567  -0.0280   1.0000   0.0110
  -6.500  -0.3377   0.07485   0.07187  -0.0308   0.9982   0.0109
  -6.250  -0.3093   0.06886   0.06585  -0.0398   0.9896   0.0107
  -6.000  -0.2775   0.06248   0.05941  -0.0495   0.9800   0.0109
  -5.750  -0.2429   0.05568   0.05254  -0.0597   0.9697   0.0114
  -5.500  -0.2105   0.05013   0.04687  -0.0678   0.9595   0.0126
  -5.250  -0.1738   0.04423   0.04079  -0.0757   0.9504   0.0133
  -5.000  -0.1350   0.03663   0.03284  -0.0838   0.9411   0.0136
  -4.750  -0.0984   0.02478   0.02016  -0.0907   0.9307   0.0142
  -4.500  -0.0663   0.01899   0.01338  -0.0930   0.9221   0.0168
  -4.250  -0.0337   0.01639   0.01002  -0.0940   0.9138   0.0210
  -4.000  -0.0028   0.01560   0.00905  -0.0947   0.9038   0.0261
  -3.750   0.0291   0.01481   0.00787  -0.0954   0.8942   0.0330
  -3.500   0.0605   0.01463   0.00759  -0.0962   0.8844   0.0394
  -3.250   0.0899   0.01386   0.00654  -0.0964   0.8736   0.0445
  -3.000   0.1187   0.01321   0.00574  -0.0965   0.8628   0.0477
  -2.750   0.1472   0.01273   0.00509  -0.0965   0.8522   0.0507
  -2.500   0.1752   0.01232   0.00450  -0.0963   0.8416   0.0532
  -2.250   0.2027   0.01200   0.00401  -0.0961   0.8307   0.0553
  -2.000   0.2294   0.01166   0.00363  -0.0958   0.8196   0.0601
  -1.750   0.2562   0.01142   0.00331  -0.0954   0.8084   0.0644
  -1.500   0.2829   0.01121   0.00298  -0.0950   0.7972   0.0693
  -1.250   0.3095   0.01101   0.00277  -0.0946   0.7855   0.0814
  -1.000   0.3359   0.01087   0.00262  -0.0942   0.7732   0.1007
  -0.750   0.3622   0.01076   0.00248  -0.0938   0.7600   0.1200
  -0.500   0.3884   0.01067   0.00237  -0.0934   0.7457   0.1383
  -0.250   0.4145   0.01056   0.00228  -0.0930   0.7304   0.1613
   0.000   0.4401   0.01037   0.00225  -0.0926   0.7133   0.2177
   0.250   0.4643   0.00995   0.00225  -0.0920   0.6947   0.3670
   0.750   0.5265   0.00873   0.00212  -0.0930   0.6534   1.0000
   1.000   0.5519   0.00888   0.00210  -0.0924   0.6326   1.0000
   1.250   0.5773   0.00904   0.00211  -0.0918   0.6126   1.0000
   1.500   0.6026   0.00922   0.00215  -0.0912   0.5945   1.0000
   1.750   0.6281   0.00941   0.00224  -0.0907   0.5783   1.0000
   2.000   0.6536   0.00961   0.00234  -0.0902   0.5639   1.0000
   2.250   0.6792   0.00980   0.00246  -0.0897   0.5508   1.0000
   2.500   0.7050   0.01000   0.00261  -0.0893   0.5392   1.0000
   2.750   0.7307   0.01021   0.00281  -0.0889   0.5285   1.0000
   3.000   0.7556   0.01045   0.00298  -0.0883   0.5103   1.0000
   3.250   0.7789   0.01076   0.00315  -0.0874   0.4779   1.0000
   3.500   0.8035   0.01101   0.00337  -0.0868   0.4555   1.0000
   3.750   0.8262   0.01137   0.00357  -0.0858   0.4122   1.0000
   4.000   0.8454   0.01208   0.00382  -0.0844   0.3217   1.0000
   4.250   0.8489   0.01502   0.00515  -0.0814   0.0271   1.0000
   4.500   0.8724   0.01555   0.00572  -0.0805   0.0194   1.0000
   4.750   0.8957   0.01609   0.00644  -0.0796   0.0158   1.0000
   5.000   0.9182   0.01675   0.00728  -0.0786   0.0142   1.0000
   5.250   0.9393   0.01756   0.00830  -0.0774   0.0132   1.0000
   5.500   0.9546   0.01902   0.01000  -0.0754   0.0117   1.0000
   5.750   0.9753   0.01975   0.01080  -0.0742   0.0106   1.0000
   6.000   0.9920   0.02092   0.01207  -0.0724   0.0101   1.0000
   6.250   1.0080   0.02221   0.01348  -0.0705   0.0098   1.0000
   6.500   1.0242   0.02362   0.01496  -0.0686   0.0096   1.0000
   6.750   1.0417   0.02516   0.01655  -0.0669   0.0094   1.0000
   7.000   1.0614   0.02686   0.01833  -0.0655   0.0093   1.0000
   7.250   1.0827   0.02853   0.02009  -0.0644   0.0089   1.0000
   7.500   1.1031   0.03011   0.02173  -0.0634   0.0078   1.0000
   7.750   1.1250   0.03286   0.02448  -0.0631   0.0071   1.0000
   8.000   1.1476   0.03556   0.02736  -0.0623   0.0070   1.0000
   8.250   1.1672   0.03776   0.02988  -0.0610   0.0071   1.0000
   8.500   1.1849   0.03998   0.03239  -0.0594   0.0072   1.0000
   8.750   1.1981   0.04246   0.03545  -0.0565   0.0080   1.0000
   9.000   1.2093   0.04619   0.03961  -0.0540   0.0090   1.0000
   9.250   1.2142   0.05027   0.04403  -0.0515   0.0100   1.0000
   9.500   1.2309   0.05319   0.04727  -0.0494   0.0139   1.0000
   9.750   1.2307   0.05637   0.05076  -0.0466   0.0139   1.0000
  10.000   1.2267   0.05952   0.05417  -0.0439   0.0139   1.0000
  10.250   1.2173   0.06245   0.05733  -0.0407   0.0138   1.0000
  10.500   1.2043   0.06539   0.06047  -0.0377   0.0137   1.0000
  10.750   1.1900   0.06857   0.06385  -0.0355   0.0137   1.0000
  11.000   1.1741   0.07220   0.06766  -0.0343   0.0137   1.0000
  11.250   1.1575   0.07624   0.07189  -0.0341   0.0136   1.0000
  11.500   1.1402   0.08079   0.07662  -0.0349   0.0137   1.0000
  11.750   1.1220   0.08593   0.08194  -0.0367   0.0137   1.0000
  12.000   1.1032   0.09177   0.08794  -0.0395   0.0138   1.0000
  12.250   1.0838   0.09841   0.09474  -0.0433   0.0139   1.0000
  12.500   1.0645   0.10586   0.10234  -0.0482   0.0141   1.0000
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