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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 200,000
Max Cl/Cd: 73.08 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe92-il-200000.txt
Download as CSV file: xf-goe92-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2635   0.09189   0.08889  -0.0248   1.0000   0.0224
  -7.250  -0.2744   0.09071   0.08781  -0.0223   1.0000   0.0225
  -7.000  -0.2944   0.09038   0.08757  -0.0179   1.0000   0.0226
  -6.750  -0.3004   0.08868   0.08592  -0.0172   0.9991   0.0228
  -6.500  -0.2699   0.08377   0.08100  -0.0256   0.9931   0.0235
  -6.250  -0.2375   0.07889   0.07608  -0.0343   0.9862   0.0244
  -6.000  -0.2005   0.07403   0.07117  -0.0441   0.9785   0.0256
  -5.750  -0.1396   0.06920   0.06615  -0.0614   0.9712   0.0268
  -5.500  -0.0956   0.06489   0.06164  -0.0707   0.9629   0.0270
  -5.250  -0.0729   0.05832   0.05509  -0.0743   0.9579   0.0277
  -5.000  -0.0543   0.05455   0.05135  -0.0753   0.9499   0.0289
  -4.750  -0.0204   0.05068   0.04738  -0.0800   0.9429   0.0306
  -4.500   0.0106   0.04723   0.04379  -0.0836   0.9321   0.0322
  -4.250   0.0479   0.04427   0.04058  -0.0873   0.9213   0.0347
  -4.000   0.0893   0.04310   0.03888  -0.0897   0.9102   0.0360
  -3.750   0.1063   0.03748   0.03326  -0.0907   0.8995   0.0373
  -3.500   0.1256   0.03494   0.03067  -0.0905   0.8864   0.0389
  -3.250   0.1491   0.03279   0.02835  -0.0903   0.8727   0.0418
  -3.000   0.1809   0.03104   0.02606  -0.0901   0.8588   0.0487
  -2.750   0.2002   0.02842   0.02346  -0.0898   0.8436   0.0519
  -2.500   0.2320   0.02938   0.02379  -0.0884   0.8264   0.0611
  -2.250   0.2510   0.02480   0.01931  -0.0888   0.8081   0.0656
  -2.000   0.2772   0.02336   0.01754  -0.0882   0.7878   0.0780
  -1.750   0.3011   0.02185   0.01588  -0.0878   0.7641   0.0940
  -1.500   0.3252   0.02066   0.01446  -0.0874   0.7370   0.1221
  -0.250   0.4647   0.01575   0.00747  -0.0824   0.6025   0.0835
   0.000   0.4922   0.01548   0.00683  -0.0814   0.5800   0.0739
   0.250   0.5184   0.01503   0.00619  -0.0808   0.5580   0.0738
   0.500   0.5443   0.01454   0.00555  -0.0801   0.5371   0.0711
   0.750   0.5702   0.01424   0.00514  -0.0795   0.5167   0.0696
   1.000   0.5960   0.01407   0.00484  -0.0790   0.4988   0.0694
   1.250   0.6219   0.01397   0.00463  -0.0786   0.4829   0.0702
   1.500   0.6481   0.01398   0.00452  -0.0783   0.4686   0.0741
   1.750   0.6746   0.01399   0.00443  -0.0780   0.4560   0.0757
   2.000   0.7012   0.01403   0.00436  -0.0777   0.4454   0.0793
   2.250   0.7279   0.01418   0.00438  -0.0775   0.4370   0.0874
   2.500   0.7565   0.01248   0.00456  -0.0778   0.4287   1.0000
   2.750   0.7830   0.01277   0.00467  -0.0775   0.4215   1.0000
   3.000   0.8095   0.01302   0.00478  -0.0772   0.4139   1.0000
   3.250   0.8358   0.01331   0.00495  -0.0770   0.4073   1.0000
   3.500   0.8622   0.01356   0.00512  -0.0768   0.4004   1.0000
   3.750   0.8885   0.01390   0.00535  -0.0766   0.3949   1.0000
   4.000   0.9149   0.01414   0.00560  -0.0765   0.3890   1.0000
   4.250   0.9412   0.01444   0.00583  -0.0763   0.3839   1.0000
   4.500   0.9676   0.01478   0.00613  -0.0762   0.3794   1.0000
   4.750   0.9939   0.01506   0.00647  -0.0760   0.3748   1.0000
   5.000   1.0202   0.01538   0.00677  -0.0759   0.3704   1.0000
   5.250   1.0465   0.01577   0.00711  -0.0758   0.3661   1.0000
   5.500   1.0723   0.01605   0.00748  -0.0756   0.3614   1.0000
   5.750   1.0983   0.01636   0.00784  -0.0754   0.3568   1.0000
   6.000   1.1233   0.01665   0.00814  -0.0751   0.3495   1.0000
   6.250   1.1469   0.01682   0.00824  -0.0745   0.3378   1.0000
   6.500   1.1705   0.01691   0.00844  -0.0740   0.3277   1.0000
   6.750   1.1949   0.01719   0.00879  -0.0736   0.3206   1.0000
   7.000   1.2181   0.01736   0.00897  -0.0730   0.3100   1.0000
   7.250   1.2400   0.01741   0.00908  -0.0721   0.2944   1.0000
   7.500   1.2628   0.01748   0.00927  -0.0715   0.2789   1.0000
   7.750   1.2854   0.01759   0.00943  -0.0708   0.2546   1.0000
   8.000   1.3049   0.01811   0.00976  -0.0698   0.1991   1.0000
   8.250   1.3133   0.01999   0.01107  -0.0677   0.1277   1.0000
   8.500   1.3245   0.02157   0.01239  -0.0658   0.0736   1.0000
   8.750   1.3282   0.02369   0.01424  -0.0630   0.0304   1.0000
   9.000   1.3405   0.02488   0.01555  -0.0610   0.0260   1.0000
   9.250   1.3528   0.02601   0.01687  -0.0591   0.0243   1.0000
   9.500   1.3620   0.02716   0.01826  -0.0567   0.0236   1.0000
   9.750   1.3685   0.02851   0.01981  -0.0542   0.0230   1.0000
  10.000   1.3724   0.03009   0.02159  -0.0518   0.0226   1.0000
  10.250   1.3736   0.03198   0.02369  -0.0496   0.0223   1.0000
  10.500   1.3724   0.03421   0.02611  -0.0476   0.0221   1.0000
  10.750   1.3687   0.03685   0.02893  -0.0461   0.0220   1.0000
  11.000   1.3629   0.03991   0.03217  -0.0450   0.0217   1.0000
  11.250   1.3558   0.04340   0.03581  -0.0445   0.0215   1.0000
  11.500   1.3477   0.04732   0.03987  -0.0446   0.0211   1.0000
  11.750   1.3391   0.05155   0.04424  -0.0451   0.0208   1.0000
  12.000   1.3307   0.05588   0.04867  -0.0457   0.0204   1.0000
  12.250   1.3231   0.06007   0.05297  -0.0461   0.0201   1.0000
  12.500   1.3180   0.06383   0.05681  -0.0462   0.0200   1.0000
  12.750   1.3155   0.06708   0.06013  -0.0459   0.0200   1.0000
  13.000   1.3166   0.06976   0.06288  -0.0450   0.0202   1.0000
  13.250   1.3227   0.07162   0.06479  -0.0434   0.0204   1.0000
  13.500   1.3356   0.07247   0.06569  -0.0407   0.0211   1.0000
  13.750   1.3532   0.07299   0.06629  -0.0374   0.0223   1.0000
  14.000   1.0834   0.09116   0.08540  -0.0356   0.0211   1.0000
  14.250   1.0877   0.09275   0.08702  -0.0343   0.0209   1.0000
  14.500   1.0992   0.09306   0.08736  -0.0321   0.0211   1.0000
  14.750   1.1164   0.09254   0.08688  -0.0290   0.0216   1.0000
  15.000   1.1356   0.09178   0.08621  -0.0253   0.0227   1.0000
  15.250   1.1940   0.08700   0.08141  -0.0175   0.0256   1.0000
  15.500   1.1742   0.09068   0.08532  -0.0184   0.0262   1.0000
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