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GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 492 AIRFOIL (goe492-il)
Reynolds number: 200,000
Max Cl/Cd: 81.36 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe492-il-200000.txt
Download as CSV file: xf-goe492-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 492 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4050   0.09236   0.08894  -0.0330   1.0000   0.0357
  -7.750  -0.4147   0.09068   0.08734  -0.0327   1.0000   0.0360
  -7.500  -0.4198   0.08827   0.08501  -0.0335   1.0000   0.0362
  -7.250  -0.4221   0.08558   0.08237  -0.0346   1.0000   0.0363
  -7.000  -0.4230   0.08261   0.07943  -0.0360   1.0000   0.0364
  -6.750  -0.4219   0.07924   0.07607  -0.0379   1.0000   0.0365
  -6.500  -0.4185   0.07561   0.07242  -0.0397   1.0000   0.0365
  -6.250  -0.4290   0.06978   0.06668  -0.0378   1.0000   0.0377
  -6.000  -0.4301   0.06889   0.06583  -0.0320   1.0000   0.0401
  -5.750  -0.4242   0.06599   0.06292  -0.0327   1.0000   0.0420
  -5.500  -0.4143   0.06223   0.05912  -0.0352   1.0000   0.0439
  -5.250  -0.3982   0.05769   0.05449  -0.0395   1.0000   0.0464
  -5.000  -0.3607   0.05182   0.04805  -0.0490   1.0000   0.0496
  -4.750  -0.3457   0.04438   0.04055  -0.0520   0.9993   0.0512
  -4.500  -0.3158   0.04108   0.03719  -0.0550   0.9962   0.0536
  -4.250  -0.2779   0.03673   0.03252  -0.0599   0.9933   0.0585
  -4.000  -0.2404   0.03187   0.02715  -0.0644   0.9898   0.0670
  -3.750  -0.1965   0.02318   0.01698  -0.0665   0.9889   0.0391
  -3.500  -0.1605   0.02092   0.01434  -0.0684   0.9861   0.0413
  -3.250  -0.1226   0.01892   0.01187  -0.0701   0.9837   0.0442
  -3.000  -0.0870   0.01765   0.01019  -0.0715   0.9803   0.0511
  -2.750  -0.0536   0.01639   0.00880  -0.0727   0.9761   0.0597
  -2.500  -0.0170   0.01545   0.00780  -0.0746   0.9724   0.0705
  -2.250   0.0224   0.01475   0.00703  -0.0770   0.9696   0.0788
  -2.000   0.0534   0.01430   0.00659  -0.0778   0.9631   0.0890
  -1.750   0.0913   0.01375   0.00603  -0.0800   0.9588   0.1024
  -1.500   0.1314   0.01290   0.00584  -0.0829   0.9559   0.2628
  -1.250   0.1613   0.01271   0.00575  -0.0834   0.9481   0.3337
  -1.000   0.2010   0.01234   0.00555  -0.0861   0.9441   0.3792
  -0.750   0.2326   0.01178   0.00547  -0.0871   0.9374   0.4888
  -0.500   0.2809   0.01056   0.00541  -0.0908   0.9357   1.0000
  -0.250   0.3244   0.01044   0.00517  -0.0939   0.9314   1.0000
   0.000   0.3642   0.01034   0.00498  -0.0963   0.9260   1.0000
   0.250   0.4006   0.01023   0.00481  -0.0979   0.9191   1.0000
   0.500   0.4427   0.01005   0.00459  -0.1006   0.9153   1.0000
   0.750   0.4722   0.00997   0.00448  -0.1006   0.9049   1.0000
   1.000   0.5043   0.00984   0.00435  -0.1011   0.8955   1.0000
   1.250   0.5400   0.00963   0.00416  -0.1022   0.8879   1.0000
   1.500   0.5678   0.00956   0.00410  -0.1018   0.8761   1.0000
   1.750   0.5954   0.00950   0.00406  -0.1014   0.8639   1.0000
   2.000   0.6229   0.00945   0.00404  -0.1009   0.8512   1.0000
   2.250   0.6501   0.00944   0.00410  -0.1004   0.8384   1.0000
   2.500   0.6770   0.00942   0.00413  -0.0998   0.8241   1.0000
   2.750   0.7031   0.00933   0.00406  -0.0988   0.8046   1.0000
   3.000   0.7253   0.00912   0.00377  -0.0964   0.7611   1.0000
   3.250   0.7461   0.00917   0.00356  -0.0939   0.6950   1.0000
   3.500   0.7653   0.00961   0.00370  -0.0914   0.6185   1.0000
   3.750   0.7555   0.01244   0.00436  -0.0844   0.2063   1.0000
   4.000   0.7651   0.01469   0.00575  -0.0814   0.0470   1.0000
   4.250   0.7843   0.01572   0.00688  -0.0797   0.0395   1.0000
   4.500   0.8011   0.01712   0.00835  -0.0775   0.0365   1.0000
   4.750   0.8216   0.01819   0.00949  -0.0759   0.0342   1.0000
   5.000   0.8431   0.01925   0.01058  -0.0746   0.0301   1.0000
   5.250   0.8657   0.02082   0.01218  -0.0734   0.0289   1.0000
   5.500   0.8917   0.02277   0.01425  -0.0726   0.0285   1.0000
   5.750   0.9215   0.02524   0.01699  -0.0718   0.0305   1.0000
   6.000   0.9511   0.02919   0.02127  -0.0709   0.0353   1.0000
   7.750   1.0711   0.05291   0.04774  -0.0553   0.0441   1.0000
   8.000   1.0786   0.05612   0.05122  -0.0533   0.0415   1.0000
   8.250   1.0858   0.05967   0.05489  -0.0518   0.0399   1.0000
   8.500   1.0956   0.06496   0.06012  -0.0514   0.0385   1.0000
   8.750   1.0817   0.07514   0.07047  -0.0503   0.0373   1.0000
   9.000   1.0760   0.07804   0.07366  -0.0476   0.0372   1.0000
   9.250   1.0661   0.08039   0.07629  -0.0448   0.0370   1.0000
   9.500   1.0514   0.08208   0.07824  -0.0416   0.0365   1.0000
   9.750   1.0308   0.08470   0.08102  -0.0386   0.0363   1.0000
  10.000   1.0100   0.08822   0.08468  -0.0375   0.0362   1.0000
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