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GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 442 AIRFOIL (goe442-il)
Reynolds number: 500,000
Max Cl/Cd: 97.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe442-il-500000.txt
Download as CSV file: xf-goe442-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 442 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3731   0.08544   0.08333  -0.0186   1.0000   0.0200
  -7.250  -0.3858   0.08380   0.08175  -0.0162   1.0000   0.0203
  -7.000  -0.3922   0.08109   0.07908  -0.0165   1.0000   0.0211
  -6.750  -0.3949   0.07732   0.07533  -0.0205   0.9999   0.0216
  -6.500  -0.3578   0.07031   0.06826  -0.0333   0.9963   0.0219
  -6.250  -0.3388   0.06465   0.06259  -0.0382   0.9936   0.0226
  -6.000  -0.3126   0.06135   0.05925  -0.0423   0.9901   0.0231
  -5.750  -0.2798   0.05705   0.05489  -0.0488   0.9868   0.0241
  -5.500  -0.2400   0.05145   0.04918  -0.0577   0.9842   0.0256
  -5.250  -0.1915   0.04233   0.03966  -0.0685   0.9783   0.0278
  -5.000  -0.1656   0.03003   0.02685  -0.0752   0.9737   0.0229
  -4.750  -0.1292   0.02903   0.02579  -0.0781   0.9718   0.0244
  -4.500  -0.1108   0.01558   0.01055  -0.0778   0.9651   0.0226
  -4.250  -0.0758   0.01472   0.00959  -0.0793   0.9618   0.0238
  -4.000  -0.0384   0.01384   0.00855  -0.0811   0.9595   0.0256
  -3.750   0.0012   0.01335   0.00788  -0.0832   0.9578   0.0279
  -3.500   0.0315   0.01226   0.00673  -0.0837   0.9529   0.0308
  -3.250   0.0642   0.01179   0.00618  -0.0844   0.9478   0.0336
  -3.000   0.0994   0.01095   0.00524  -0.0856   0.9439   0.0373
  -2.750   0.1286   0.01074   0.00504  -0.0856   0.9364   0.0407
  -2.500   0.1612   0.01043   0.00467  -0.0862   0.9295   0.0442
  -2.250   0.1886   0.00976   0.00396  -0.0859   0.9192   0.0481
  -2.000   0.2185   0.00945   0.00364  -0.0860   0.9082   0.0518
  -1.750   0.2479   0.00923   0.00337  -0.0859   0.8949   0.0556
  -1.500   0.2759   0.00882   0.00290  -0.0856   0.8778   0.0586
  -1.250   0.3039   0.00847   0.00250  -0.0853   0.8564   0.0635
  -1.000   0.3310   0.00830   0.00224  -0.0847   0.8293   0.0677
  -0.750   0.3572   0.00824   0.00203  -0.0840   0.7976   0.0710
  -0.500   0.3815   0.00811   0.00175  -0.0829   0.7593   0.0789
  -0.250   0.4047   0.00821   0.00161  -0.0816   0.7114   0.0851
   0.000   0.4269   0.00827   0.00150  -0.0802   0.6592   0.1027
   0.250   0.4474   0.00795   0.00156  -0.0788   0.6103   0.3042
   0.500   0.5049   0.00655   0.00170  -0.0857   0.5689   1.0000
   1.000   0.5522   0.00698   0.00178  -0.0837   0.5248   1.0000
   1.250   0.5767   0.00715   0.00183  -0.0828   0.5098   1.0000
   1.500   0.6013   0.00732   0.00189  -0.0820   0.4947   1.0000
   1.750   0.6260   0.00748   0.00196  -0.0812   0.4799   1.0000
   2.000   0.6508   0.00764   0.00203  -0.0805   0.4658   1.0000
   2.250   0.6757   0.00779   0.00210  -0.0797   0.4517   1.0000
   2.750   0.7259   0.00808   0.00226  -0.0784   0.4251   1.0000
   3.000   0.7511   0.00822   0.00236  -0.0777   0.4133   1.0000
   3.250   0.7763   0.00837   0.00246  -0.0771   0.4016   1.0000
   3.500   0.8013   0.00854   0.00257  -0.0764   0.3897   1.0000
   3.750   0.8261   0.00872   0.00271  -0.0757   0.3776   1.0000
   4.000   0.8512   0.00889   0.00284  -0.0751   0.3651   1.0000
   4.250   0.8762   0.00906   0.00298  -0.0745   0.3519   1.0000
   4.500   0.9009   0.00926   0.00313  -0.0738   0.3371   1.0000
   4.750   0.9254   0.00949   0.00331  -0.0731   0.3211   1.0000
   5.000   0.9497   0.00973   0.00349  -0.0724   0.3034   1.0000
   5.250   0.9737   0.01000   0.00369  -0.0716   0.2796   1.0000
   5.500   0.9964   0.01042   0.00395  -0.0707   0.2425   1.0000
   5.750   1.0169   0.01107   0.00433  -0.0695   0.1926   1.0000
   6.000   1.0385   0.01163   0.00473  -0.0684   0.1685   1.0000
   6.250   1.0613   0.01205   0.00511  -0.0675   0.1578   1.0000
   6.500   1.0837   0.01250   0.00553  -0.0665   0.1505   1.0000
   6.750   1.1071   0.01284   0.00590  -0.0657   0.1458   1.0000
   7.000   1.1303   0.01319   0.00628  -0.0649   0.1414   1.0000
   7.250   1.1517   0.01370   0.00676  -0.0638   0.1357   1.0000
   7.500   1.1757   0.01395   0.00708  -0.0632   0.1308   1.0000
   7.750   1.1984   0.01431   0.00744  -0.0623   0.1248   1.0000
   8.000   1.2202   0.01475   0.00789  -0.0614   0.1199   1.0000
   8.250   1.2441   0.01497   0.00820  -0.0607   0.1158   1.0000
   8.500   1.2662   0.01535   0.00860  -0.0598   0.1110   1.0000
   8.750   1.2880   0.01575   0.00904  -0.0589   0.1061   1.0000
   9.000   1.3120   0.01594   0.00931  -0.0583   0.1008   1.0000
   9.250   1.3335   0.01633   0.00970  -0.0574   0.0934   1.0000
   9.500   1.3569   0.01658   0.00995  -0.0567   0.0786   1.0000
   9.750   1.3657   0.01810   0.01106  -0.0541   0.0334   1.0000
  10.000   1.3775   0.01931   0.01225  -0.0516   0.0238   1.0000
  10.250   1.3921   0.02019   0.01321  -0.0496   0.0207   1.0000
  10.500   1.4021   0.02138   0.01448  -0.0470   0.0184   1.0000
  10.750   1.4152   0.02215   0.01536  -0.0447   0.0173   1.0000
  11.000   1.4247   0.02303   0.01633  -0.0420   0.0161   1.0000
  11.250   1.4310   0.02408   0.01746  -0.0389   0.0151   1.0000
  11.500   1.4303   0.02556   0.01905  -0.0351   0.0143   1.0000
  11.750   1.4299   0.02709   0.02071  -0.0316   0.0138   1.0000
  12.000   1.4347   0.02835   0.02208  -0.0290   0.0134   1.0000
  12.250   1.4373   0.02982   0.02368  -0.0265   0.0130   1.0000
  12.500   1.4383   0.03150   0.02548  -0.0242   0.0126   1.0000
  12.750   1.4371   0.03350   0.02759  -0.0221   0.0122   1.0000
  13.000   1.4357   0.03567   0.02988  -0.0205   0.0119   1.0000
  13.250   1.4325   0.03821   0.03254  -0.0192   0.0117   1.0000
  13.500   1.4286   0.04105   0.03551  -0.0185   0.0114   1.0000
  13.750   1.4234   0.04429   0.03886  -0.0183   0.0112   1.0000
  14.000   1.4135   0.04837   0.04305  -0.0187   0.0109   1.0000
  14.250   1.4061   0.05240   0.04721  -0.0194   0.0108   1.0000
  14.500   1.3957   0.05703   0.05197  -0.0205   0.0107   1.0000
  14.750   1.3775   0.06280   0.05788  -0.0218   0.0103   1.0000
  15.000   1.3722   0.06707   0.06228  -0.0233   0.0102   1.0000
  15.250   1.3674   0.07148   0.06683  -0.0251   0.0101   1.0000
  15.500   1.3605   0.07620   0.07168  -0.0270   0.0100   1.0000
  15.750   1.3518   0.08126   0.07688  -0.0290   0.0099   1.0000
  16.000   1.3435   0.08648   0.08223  -0.0312   0.0098   1.0000
  16.250   1.3349   0.09187   0.08775  -0.0336   0.0096   1.0000
  16.500   1.3253   0.09746   0.09347  -0.0361   0.0096   1.0000
  16.750   1.3159   0.10326   0.09940  -0.0389   0.0095   1.0000
  17.000   1.3064   0.10918   0.10545  -0.0417   0.0094   1.0000
  17.250   1.2968   0.11527   0.11167  -0.0449   0.0093   1.0000
  17.500   1.2875   0.12149   0.11800  -0.0482   0.0092   1.0000
  17.750   1.2771   0.12799   0.12464  -0.0516   0.0093   1.0000
  18.000   1.2673   0.13462   0.13140  -0.0554   0.0092   1.0000
  18.250   1.2558   0.14171   0.13862  -0.0595   0.0092   1.0000
  18.500   1.2456   0.14875   0.14578  -0.0637   0.0091   1.0000
  18.750   1.2337   0.15639   0.15356  -0.0684   0.0091   1.0000
  19.000   1.2209   0.16454   0.16184  -0.0735   0.0091   1.0000
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