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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 500,000
Max Cl/Cd: 102.1 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe397-il-500000-n5.txt
Download as CSV file: xf-goe397-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3866   0.08950   0.08729  -0.0198   1.0000   0.0065
  -7.750  -0.3869   0.08631   0.08414  -0.0205   1.0000   0.0068
  -7.500  -0.3883   0.08357   0.08144  -0.0208   1.0000   0.0068
  -7.250  -0.3844   0.08058   0.07847  -0.0223   1.0000   0.0067
  -7.000  -0.3795   0.07707   0.07500  -0.0245   1.0000   0.0067
  -6.750  -0.3682   0.07305   0.07099  -0.0283   0.9979   0.0067
  -6.500  -0.3431   0.06751   0.06539  -0.0363   0.9865   0.0067
  -6.250  -0.3119   0.06066   0.05848  -0.0461   0.9752   0.0069
  -6.000  -0.2769   0.05357   0.05129  -0.0562   0.9615   0.0071
  -5.750  -0.2419   0.04977   0.04739  -0.0627   0.9478   0.0078
  -5.500  -0.2064   0.04535   0.04283  -0.0690   0.9301   0.0087
  -5.250  -0.1734   0.03841   0.03561  -0.0752   0.9074   0.0097
  -5.000  -0.1457   0.02959   0.02628  -0.0793   0.8855   0.0109
  -4.750  -0.1208   0.02741   0.02387  -0.0798   0.8686   0.0117
  -4.500  -0.1002   0.01635   0.01159  -0.0798   0.8549   0.0167
  -4.000  -0.0481   0.01653   0.01163  -0.0794   0.8314   0.0185
  -3.750  -0.0218   0.01690   0.01195  -0.0792   0.8211   0.0199
  -3.500   0.0039   0.01595   0.01076  -0.0788   0.8117   0.0219
  -3.250   0.0297   0.01490   0.00943  -0.0784   0.8022   0.0240
  -3.000   0.0560   0.01419   0.00850  -0.0780   0.7927   0.0255
  -2.750   0.0822   0.01352   0.00759  -0.0776   0.7833   0.0262
  -2.500   0.1089   0.01335   0.00729  -0.0773   0.7736   0.0269
  -2.250   0.1354   0.01273   0.00648  -0.0770   0.7644   0.0274
  -2.000   0.1606   0.01114   0.00464  -0.0765   0.7541   0.0291
  -1.750   0.1866   0.01068   0.00406  -0.0761   0.7394   0.0303
  -1.500   0.2126   0.01037   0.00364  -0.0757   0.7222   0.0315
  -1.250   0.2387   0.01008   0.00325  -0.0753   0.7067   0.0324
  -1.000   0.2649   0.00982   0.00289  -0.0749   0.6934   0.0331
  -0.750   0.2911   0.00958   0.00257  -0.0745   0.6811   0.0335
  -0.500   0.3173   0.00938   0.00229  -0.0741   0.6711   0.0340
  -0.250   0.3439   0.00922   0.00210  -0.0738   0.6627   0.0350
   0.000   0.3704   0.00904   0.00188  -0.0735   0.6554   0.0352
   0.250   0.3969   0.00887   0.00168  -0.0731   0.6484   0.0349
   0.500   0.4235   0.00875   0.00152  -0.0728   0.6422   0.0347
   0.750   0.4503   0.00863   0.00140  -0.0726   0.6355   0.0345
   1.250   0.5039   0.00851   0.00125  -0.0720   0.6231   0.0344
   1.500   0.5307   0.00848   0.00122  -0.0718   0.6172   0.0344
   1.750   0.5576   0.00847   0.00120  -0.0716   0.6112   0.0346
   2.000   0.5844   0.00848   0.00120  -0.0713   0.6034   0.0351
   2.250   0.6107   0.00852   0.00122  -0.0709   0.5882   0.0360
   2.500   0.6369   0.00857   0.00125  -0.0706   0.5716   0.0383
   3.000   0.7055   0.00691   0.00157  -0.0742   0.5151   1.0000
   3.250   0.7275   0.00736   0.00171  -0.0732   0.4432   1.0000
   3.500   0.7497   0.00789   0.00195  -0.0722   0.3846   1.0000
   3.750   0.7738   0.00824   0.00217  -0.0716   0.3497   1.0000
   4.000   0.7977   0.00861   0.00241  -0.0709   0.3151   1.0000
   4.250   0.8208   0.00908   0.00270  -0.0702   0.2633   1.0000
   4.500   0.8369   0.01044   0.00336  -0.0686   0.1159   1.0000
   4.750   0.8585   0.01113   0.00380  -0.0677   0.0665   1.0000
   5.000   0.8825   0.01151   0.00413  -0.0671   0.0542   1.0000
   5.250   0.9069   0.01182   0.00446  -0.0665   0.0461   1.0000
   5.500   0.9309   0.01218   0.00481  -0.0659   0.0380   1.0000
   5.750   0.9545   0.01258   0.00518  -0.0653   0.0258   1.0000
   6.000   0.9773   0.01309   0.00563  -0.0645   0.0159   1.0000
   6.250   0.9994   0.01371   0.00631  -0.0634   0.0113   1.0000
   6.500   1.0224   0.01417   0.00687  -0.0626   0.0100   1.0000
   6.750   1.0447   0.01469   0.00746  -0.0618   0.0086   1.0000
   7.000   1.0657   0.01538   0.00822  -0.0607   0.0077   1.0000
   7.250   1.0846   0.01634   0.00929  -0.0593   0.0069   1.0000
   7.500   1.1047   0.01710   0.01017  -0.0580   0.0065   1.0000
   7.750   1.1244   0.01791   0.01108  -0.0568   0.0060   1.0000
   8.000   1.1442   0.01868   0.01196  -0.0556   0.0055   1.0000
   8.250   1.1644   0.01934   0.01266  -0.0547   0.0050   1.0000
   8.500   1.1807   0.02051   0.01392  -0.0531   0.0046   1.0000
   8.750   1.1955   0.02197   0.01553  -0.0512   0.0044   1.0000
   9.000   1.2128   0.02309   0.01682  -0.0497   0.0042   1.0000
   9.250   1.2281   0.02456   0.01848  -0.0480   0.0041   1.0000
   9.500   1.2428   0.02613   0.02025  -0.0463   0.0039   1.0000
   9.750   1.2562   0.02786   0.02221  -0.0444   0.0037   1.0000
  10.000   1.2678   0.02977   0.02435  -0.0425   0.0035   1.0000
  10.250   1.2763   0.03204   0.02689  -0.0402   0.0034   1.0000
  10.500   1.2815   0.03437   0.02950  -0.0376   0.0033   1.0000
  10.750   1.2817   0.03661   0.03203  -0.0344   0.0033   1.0000
  11.000   1.2769   0.03923   0.03492  -0.0310   0.0032   1.0000
  11.250   1.2688   0.04214   0.03809  -0.0280   0.0032   1.0000
  11.500   1.2645   0.04443   0.04055  -0.0259   0.0031   1.0000
  11.750   1.2559   0.04745   0.04377  -0.0243   0.0031   1.0000
  12.000   1.2458   0.05085   0.04736  -0.0234   0.0030   1.0000
  12.250   1.2133   0.05810   0.05499  -0.0234   0.0031   1.0000
  12.500   1.2031   0.06224   0.05928  -0.0244   0.0031   1.0000
  12.750   1.1947   0.06641   0.06356  -0.0260   0.0030   1.0000
  13.000   1.1406   0.08002   0.07757  -0.0322   0.0032   1.0000
  13.250   1.1111   0.09070   0.08839  -0.0388   0.0032   1.0000
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