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GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 432 AIRFOIL (goe432-il)
Reynolds number: 500,000
Max Cl/Cd: 94.79 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe432-il-500000.txt
Download as CSV file: xf-goe432-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 432 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  -0.3775   0.08576   0.08366  -0.0178   1.0000   0.0203
  -7.250  -0.3893   0.08396   0.08191  -0.0157   1.0000   0.0205
  -7.000  -0.3953   0.08062   0.07862  -0.0184   1.0000   0.0213
  -6.750  -0.3943   0.07676   0.07477  -0.0223   1.0000   0.0216
  -6.500  -0.3704   0.07121   0.06917  -0.0302   0.9979   0.0217
  -6.250  -0.3523   0.06586   0.06382  -0.0343   0.9952   0.0224
  -6.000  -0.3246   0.06231   0.06023  -0.0390   0.9922   0.0229
  -5.750  -0.2919   0.05787   0.05574  -0.0458   0.9883   0.0238
  -5.500  -0.2510   0.05210   0.04985  -0.0550   0.9851   0.0255
  -5.250  -0.1984   0.04264   0.04000  -0.0669   0.9803   0.0276
  -5.000  -0.1740   0.02884   0.02559  -0.0735   0.9746   0.0209
  -4.750  -0.1422   0.01947   0.01511  -0.0766   0.9716   0.0213
  -4.500  -0.1142   0.01577   0.01077  -0.0771   0.9673   0.0225
  -4.250  -0.0815   0.01515   0.01008  -0.0781   0.9629   0.0237
  -4.000  -0.0453   0.01420   0.00895  -0.0797   0.9602   0.0255
  -3.750  -0.0075   0.01321   0.00771  -0.0815   0.9583   0.0281
  -3.500   0.0328   0.01250   0.00698  -0.0841   0.9565   0.0308
  -3.250   0.0615   0.01198   0.00639  -0.0838   0.9483   0.0334
  -3.000   0.0979   0.01108   0.00537  -0.0853   0.9433   0.0371
  -2.750   0.1262   0.01078   0.00508  -0.0851   0.9342   0.0405
  -2.500   0.1598   0.01040   0.00465  -0.0859   0.9272   0.0440
  -2.250   0.1859   0.00972   0.00391  -0.0852   0.9143   0.0476
  -2.000   0.2146   0.00929   0.00348  -0.0851   0.8997   0.0513
  -1.750   0.2444   0.00900   0.00313  -0.0851   0.8814   0.0551
  -1.500   0.2747   0.00876   0.00278  -0.0852   0.8565   0.0573
  -1.250   0.3021   0.00835   0.00223  -0.0847   0.8244   0.0621
  -1.000   0.3279   0.00827   0.00199  -0.0839   0.7893   0.0661
  -0.750   0.3524   0.00829   0.00182  -0.0829   0.7518   0.0701
  -0.500   0.3760   0.00828   0.00165  -0.0817   0.7096   0.0777
  -0.250   0.3991   0.00835   0.00155  -0.0805   0.6628   0.0904
   0.000   0.4204   0.00806   0.00155  -0.0792   0.6167   0.2496
   0.250   0.4418   0.00782   0.00160  -0.0780   0.5793   0.4139
   0.500   0.5020   0.00671   0.00171  -0.0852   0.5461   1.0000
   0.750   0.5260   0.00690   0.00175  -0.0843   0.5269   1.0000
   1.000   0.5504   0.00708   0.00179  -0.0834   0.5093   1.0000
   1.250   0.5751   0.00724   0.00184  -0.0826   0.4942   1.0000
   1.500   0.5999   0.00739   0.00189  -0.0818   0.4807   1.0000
   1.750   0.6247   0.00754   0.00196  -0.0811   0.4680   1.0000
   2.000   0.6499   0.00767   0.00202  -0.0804   0.4552   1.0000
   2.250   0.6751   0.00781   0.00209  -0.0797   0.4426   1.0000
   2.500   0.7001   0.00796   0.00217  -0.0790   0.4288   1.0000
   2.750   0.7251   0.00811   0.00226  -0.0783   0.4142   1.0000
   3.000   0.7500   0.00827   0.00235  -0.0776   0.3994   1.0000
   3.250   0.7750   0.00844   0.00245  -0.0769   0.3856   1.0000
   3.500   0.7998   0.00862   0.00256  -0.0763   0.3715   1.0000
   3.750   0.8247   0.00880   0.00270  -0.0756   0.3570   1.0000
   4.000   0.8495   0.00900   0.00284  -0.0749   0.3423   1.0000
   4.250   0.8740   0.00922   0.00299  -0.0742   0.3248   1.0000
   4.500   0.8980   0.00948   0.00316  -0.0734   0.3019   1.0000
   4.750   0.9216   0.00980   0.00336  -0.0726   0.2716   1.0000
   5.000   0.9444   0.01022   0.00360  -0.0717   0.2355   1.0000
   5.250   0.9673   0.01063   0.00387  -0.0708   0.2112   1.0000
   5.500   0.9908   0.01098   0.00417  -0.0700   0.1994   1.0000
   5.750   1.0141   0.01134   0.00448  -0.0691   0.1919   1.0000
   6.000   1.0383   0.01161   0.00477  -0.0684   0.1872   1.0000
   6.250   1.0618   0.01194   0.00510  -0.0676   0.1826   1.0000
   6.500   1.0844   0.01236   0.00550  -0.0667   0.1779   1.0000
   6.750   1.1088   0.01260   0.00582  -0.0660   0.1749   1.0000
   7.000   1.1323   0.01292   0.00617  -0.0652   0.1698   1.0000
   7.250   1.1537   0.01343   0.00664  -0.0642   0.1632   1.0000
   7.500   1.1787   0.01358   0.00689  -0.0637   0.1570   1.0000
   7.750   1.2001   0.01406   0.00733  -0.0627   0.1487   1.0000
   8.000   1.2255   0.01415   0.00753  -0.0623   0.1433   1.0000
   8.250   1.2484   0.01448   0.00785  -0.0615   0.1362   1.0000
   8.500   1.2729   0.01465   0.00811  -0.0609   0.1281   1.0000
   8.750   1.2963   0.01493   0.00839  -0.0602   0.1177   1.0000
   9.000   1.3185   0.01530   0.00870  -0.0594   0.1010   1.0000
   9.250   1.3372   0.01598   0.00925  -0.0581   0.0816   1.0000
   9.500   1.3499   0.01719   0.01022  -0.0559   0.0449   1.0000
   9.750   1.3594   0.01866   0.01153  -0.0532   0.0258   1.0000
  10.000   1.3749   0.01953   0.01248  -0.0513   0.0218   1.0000
  10.250   1.3857   0.02072   0.01375  -0.0487   0.0190   1.0000
  10.500   1.4006   0.02149   0.01462  -0.0467   0.0177   1.0000
  10.750   1.4124   0.02234   0.01556  -0.0443   0.0165   1.0000
  11.000   1.4193   0.02336   0.01667  -0.0412   0.0154   1.0000
  11.250   1.4191   0.02479   0.01821  -0.0372   0.0146   1.0000
  11.500   1.4221   0.02607   0.01961  -0.0340   0.0140   1.0000
  11.750   1.4271   0.02726   0.02092  -0.0312   0.0136   1.0000
  12.000   1.4299   0.02865   0.02243  -0.0284   0.0132   1.0000
  12.250   1.4324   0.03015   0.02403  -0.0259   0.0127   1.0000
  12.500   1.4322   0.03194   0.02594  -0.0236   0.0124   1.0000
  12.750   1.4309   0.03395   0.02807  -0.0216   0.0121   1.0000
  13.000   1.4280   0.03630   0.03053  -0.0200   0.0118   1.0000
  13.250   1.4238   0.03900   0.03333  -0.0189   0.0115   1.0000
  13.500   1.4176   0.04215   0.03660  -0.0183   0.0113   1.0000
  13.750   1.4074   0.04606   0.04064  -0.0182   0.0110   1.0000
  14.000   1.3963   0.05037   0.04508  -0.0187   0.0108   1.0000
  14.250   1.3837   0.05509   0.04994  -0.0193   0.0107   1.0000
  14.500   1.3794   0.05905   0.05405  -0.0205   0.0105   1.0000
  14.750   1.3755   0.06309   0.05823  -0.0219   0.0103   1.0000
  15.000   1.3701   0.06742   0.06269  -0.0235   0.0102   1.0000
  15.250   1.3623   0.07219   0.06759  -0.0252   0.0100   1.0000
  15.500   1.3541   0.07703   0.07256  -0.0269   0.0100   1.0000
  15.750   1.3470   0.08195   0.07761  -0.0290   0.0098   1.0000
  16.000   1.3382   0.08720   0.08299  -0.0312   0.0097   1.0000
  16.250   1.3293   0.09262   0.08854  -0.0336   0.0096   1.0000
  16.500   1.3197   0.09824   0.09429  -0.0361   0.0096   1.0000
  16.750   1.3110   0.10393   0.10011  -0.0389   0.0095   1.0000
  17.000   1.3012   0.10992   0.10623  -0.0417   0.0094   1.0000
  17.250   1.2916   0.11609   0.11252  -0.0450   0.0093   1.0000
  17.500   1.2808   0.12256   0.11913  -0.0484   0.0093   1.0000
  17.750   1.2711   0.12907   0.12576  -0.0520   0.0092   1.0000
  18.000   1.2612   0.13573   0.13255  -0.0558   0.0091   1.0000
  18.250   1.2511   0.14259   0.13953  -0.0598   0.0091   1.0000
  18.500   1.2387   0.15019   0.14727  -0.0644   0.0091   1.0000
  18.750   1.2245   0.15857   0.15580  -0.0695   0.0092   1.0000
  19.000   1.2116   0.16687   0.16424  -0.0748   0.0092   1.0000
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