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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 100,000
Max Cl/Cd: 52.66 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe585-il-100000.txt
Download as CSV file: xf-goe585-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3947   0.09916   0.09410  -0.0255   1.0000   0.0988
  -8.250  -0.4172   0.09853   0.09362  -0.0284   1.0000   0.0999
  -8.000  -0.4342   0.09686   0.09205  -0.0343   1.0000   0.1004
  -7.750  -0.3981   0.08987   0.08501  -0.0253   1.0000   0.1035
  -7.500  -0.3941   0.08717   0.08236  -0.0239   1.0000   0.1067
  -7.250  -0.3988   0.08483   0.08010  -0.0238   1.0000   0.1102
  -7.000  -0.4123   0.08273   0.07808  -0.0297   1.0000   0.1141
  -6.750  -0.4177   0.07891   0.07428  -0.0329   1.0000   0.1159
  -6.500  -0.4057   0.07600   0.07145  -0.0259   1.0000   0.1194
  -6.250  -0.4029   0.07348   0.06895  -0.0251   1.0000   0.1237
  -6.000  -0.4078   0.07014   0.06545  -0.0335   1.0000   0.1307
  -5.750  -0.4017   0.06683   0.06226  -0.0289   1.0000   0.1325
  -5.500  -0.3957   0.06442   0.05989  -0.0263   1.0000   0.1358
  -5.250  -0.3878   0.06105   0.05626  -0.0317   1.0000   0.1462
  -5.000  -0.3814   0.05820   0.05354  -0.0282   1.0000   0.1486
  -4.750  -0.3717   0.05604   0.05135  -0.0272   1.0000   0.1567
  -4.500  -0.3624   0.05309   0.04835  -0.0271   1.0000   0.1653
  -4.250  -0.3495   0.05043   0.04555  -0.0280   1.0000   0.1784
  -4.000  -0.3350   0.04824   0.04319  -0.0285   1.0000   0.1924
  -3.750  -0.3243   0.04584   0.04087  -0.0263   1.0000   0.1968
  -3.500  -0.2723   0.03530   0.02854  -0.0345   1.0000   0.1145
  -3.250  -0.2534   0.03239   0.02559  -0.0340   1.0000   0.1113
  -3.000  -0.2256   0.02870   0.02099  -0.0338   1.0000   0.0991
  -2.750  -0.2035   0.02672   0.01873  -0.0332   1.0000   0.0976
  -2.500  -0.1813   0.02518   0.01685  -0.0324   1.0000   0.0970
  -2.250  -0.1595   0.02418   0.01549  -0.0315   1.0000   0.0990
  -2.000  -0.1380   0.02321   0.01423  -0.0306   1.0000   0.1012
  -1.750  -0.1048   0.02216   0.01309  -0.0320   0.9963   0.1039
  -1.500  -0.0539   0.02138   0.01219  -0.0363   0.9864   0.1100
  -1.250  -0.0047   0.02059   0.01138  -0.0403   0.9757   0.1206
  -1.000   0.0405   0.01992   0.01076  -0.0436   0.9658   0.1442
  -0.750   0.0854   0.01870   0.01008  -0.0468   0.9580   0.2237
  -0.500   0.1499   0.01608   0.00988  -0.0535   0.9543   1.0000
  -0.250   0.1981   0.01622   0.00967  -0.0574   0.9441   1.0000
   0.000   0.2405   0.01627   0.00950  -0.0601   0.9321   1.0000
   0.250   0.2842   0.01627   0.00934  -0.0629   0.9204   1.0000
   0.500   0.3337   0.01613   0.00908  -0.0667   0.9100   1.0000
   0.750   0.3868   0.01582   0.00868  -0.0709   0.8998   1.0000
   1.000   0.4299   0.01554   0.00835  -0.0731   0.8865   1.0000
   1.250   0.4716   0.01521   0.00798  -0.0749   0.8724   1.0000
   1.500   0.5111   0.01485   0.00758  -0.0760   0.8570   1.0000
   1.750   0.5484   0.01446   0.00718  -0.0767   0.8400   1.0000
   2.000   0.5794   0.01418   0.00687  -0.0761   0.8194   1.0000
   2.250   0.6095   0.01390   0.00655  -0.0753   0.7961   1.0000
   2.500   0.6374   0.01370   0.00631  -0.0741   0.7687   1.0000
   2.750   0.6649   0.01358   0.00609  -0.0728   0.7373   1.0000
   3.000   0.6906   0.01359   0.00595  -0.0713   0.7003   1.0000
   3.250   0.7142   0.01374   0.00592  -0.0695   0.6577   1.0000
   3.500   0.7359   0.01401   0.00598  -0.0676   0.6109   1.0000
   3.750   0.7572   0.01438   0.00610  -0.0658   0.5659   1.0000
   4.000   0.7787   0.01485   0.00632  -0.0641   0.5265   1.0000
   4.250   0.8008   0.01539   0.00664  -0.0627   0.4944   1.0000
   4.500   0.8234   0.01599   0.00705  -0.0615   0.4669   1.0000
   4.750   0.8467   0.01664   0.00753  -0.0606   0.4443   1.0000
   5.000   0.8705   0.01730   0.00810  -0.0597   0.4245   1.0000
   5.250   0.8945   0.01798   0.00872  -0.0589   0.4072   1.0000
   5.500   0.9187   0.01868   0.00936  -0.0582   0.3916   1.0000
   5.750   0.9430   0.01939   0.01007  -0.0575   0.3777   1.0000
   6.000   0.9671   0.02011   0.01082  -0.0568   0.3648   1.0000
   6.250   0.9909   0.02082   0.01156  -0.0560   0.3519   1.0000
   6.500   1.0135   0.02143   0.01218  -0.0550   0.3377   1.0000
   6.750   1.0356   0.02200   0.01277  -0.0540   0.3233   1.0000
   7.000   1.0581   0.02260   0.01340  -0.0530   0.3103   1.0000
   7.250   1.0805   0.02319   0.01403  -0.0521   0.2978   1.0000
   7.500   1.1013   0.02376   0.01475  -0.0508   0.2847   1.0000
   7.750   1.1217   0.02431   0.01543  -0.0495   0.2712   1.0000
   8.000   1.1412   0.02480   0.01601  -0.0481   0.2564   1.0000
   8.250   1.1594   0.02518   0.01646  -0.0464   0.2399   1.0000
   8.500   1.1736   0.02543   0.01681  -0.0441   0.2199   1.0000
   8.750   1.1854   0.02561   0.01705  -0.0416   0.1971   1.0000
   9.000   1.1956   0.02610   0.01761  -0.0388   0.1713   1.0000
   9.250   1.2041   0.02692   0.01840  -0.0360   0.1434   1.0000
   9.500   1.2115   0.02816   0.01958  -0.0331   0.1176   1.0000
   9.750   1.2167   0.02986   0.02109  -0.0301   0.0980   1.0000
  10.000   1.2233   0.03180   0.02299  -0.0273   0.0842   1.0000
  10.250   1.2331   0.03413   0.02514  -0.0252   0.0752   1.0000
  10.500   1.2430   0.03594   0.02720  -0.0228   0.0685   1.0000
  10.750   1.2584   0.03858   0.02974  -0.0217   0.0628   1.0000
  11.000   1.2701   0.04078   0.03224  -0.0197   0.0595   1.0000
  11.250   1.2822   0.04319   0.03489  -0.0180   0.0567   1.0000
  11.500   1.2980   0.04599   0.03770  -0.0172   0.0539   1.0000
  11.750   1.3046   0.04961   0.04156  -0.0155   0.0519   1.0000
  12.000   1.2978   0.05188   0.04418  -0.0120   0.0509   1.0000
  12.250   1.2897   0.05466   0.04730  -0.0091   0.0501   1.0000
  12.500   1.2783   0.05783   0.05078  -0.0065   0.0495   1.0000
  12.750   1.2649   0.06139   0.05464  -0.0047   0.0494   1.0000
  13.000   1.2474   0.06543   0.05896  -0.0036   0.0493   1.0000
  13.250   1.2274   0.07001   0.06382  -0.0035   0.0493   1.0000
  13.500   1.2049   0.07526   0.06932  -0.0045   0.0495   1.0000
  13.750   1.1807   0.08129   0.07558  -0.0067   0.0499   1.0000
  14.000   1.1538   0.08836   0.08287  -0.0103   0.0503   1.0000
  14.250   1.1262   0.09647   0.09115  -0.0152   0.0509   1.0000
  14.500   1.0967   0.10585   0.10068  -0.0212   0.0515   1.0000
  14.750   1.0694   0.11596   0.11087  -0.0274   0.0523   1.0000
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