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GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 459 AIRFOIL (goe459-il)
Reynolds number: 100,000
Max Cl/Cd: 40.46 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe459-il-100000.txt
Download as CSV file: xf-goe459-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 459 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7951   0.08291   0.07730  -0.0459   1.0000   0.0816
 -12.750  -0.8261   0.07562   0.06993  -0.0490   1.0000   0.0809
 -12.500  -0.8572   0.06958   0.06377  -0.0507   1.0000   0.0802
 -12.250  -0.8891   0.06454   0.05855  -0.0505   1.0000   0.0798
 -12.000  -0.9188   0.06047   0.05429  -0.0485   1.0000   0.0796
 -11.750  -0.9476   0.05716   0.05077  -0.0446   1.0000   0.0798
 -11.500  -0.9728   0.05432   0.04769  -0.0394   1.0000   0.0800
 -11.250  -0.9956   0.05139   0.04441  -0.0342   1.0000   0.0809
 -11.000  -1.0151   0.04893   0.04149  -0.0286   1.0000   0.0820
 -10.750  -0.9951   0.04657   0.03937  -0.0285   1.0000   0.0870
 -10.500  -0.9951   0.04464   0.03722  -0.0251   1.0000   0.0906
 -10.250  -1.0024   0.04243   0.03453  -0.0204   1.0000   0.0935
 -10.000  -0.9962   0.04005   0.03201  -0.0178   1.0000   0.0972
  -9.750  -0.9812   0.03897   0.03094  -0.0161   1.0000   0.1021
  -9.500  -0.9770   0.03746   0.02905  -0.0125   1.0000   0.1063
  -9.250  -0.9653   0.03567   0.02714  -0.0103   1.0000   0.1105
  -9.000  -0.9494   0.03465   0.02609  -0.0086   1.0000   0.1154
  -8.750  -0.9382   0.03334   0.02447  -0.0058   1.0000   0.1194
  -8.500  -0.9243   0.03171   0.02254  -0.0035   1.0000   0.1223
  -8.250  -0.9033   0.03025   0.02115  -0.0026   1.0000   0.1261
  -7.750  -0.8668   0.02793   0.01847   0.0009   1.0000   0.1337
  -7.500  -0.8455   0.02659   0.01702   0.0020   1.0000   0.1372
  -7.250  -0.8241   0.02550   0.01602   0.0031   1.0000   0.1419
  -7.000  -0.8054   0.02463   0.01504   0.0048   1.0000   0.1480
  -6.750  -0.7852   0.02354   0.01400   0.0061   1.0000   0.1544
  -6.500  -0.7668   0.02267   0.01313   0.0079   1.0000   0.1630
  -6.250  -0.7500   0.02168   0.01229   0.0099   1.0000   0.1734
  -6.000  -0.7359   0.02074   0.01149   0.0123   1.0000   0.1902
  -5.750  -0.7254   0.01978   0.01079   0.0154   1.0000   0.2187
  -5.500  -0.7165   0.01894   0.01021   0.0187   1.0000   0.2597
  -5.250  -0.7066   0.01824   0.00973   0.0219   1.0000   0.3008
  -5.000  -0.6957   0.01761   0.00932   0.0249   1.0000   0.3393
  -4.750  -0.6844   0.01707   0.00902   0.0278   1.0000   0.3789
  -4.500  -0.6728   0.01666   0.00884   0.0308   1.0000   0.4220
  -4.250  -0.6608   0.01634   0.00872   0.0338   1.0000   0.4683
  -4.000  -0.6485   0.01607   0.00863   0.0368   1.0000   0.5143
  -3.750  -0.6361   0.01587   0.00861   0.0398   1.0000   0.5604
  -3.500  -0.6235   0.01576   0.00868   0.0429   1.0000   0.6056
  -3.250  -0.6099   0.01572   0.00881   0.0459   1.0000   0.6472
  -3.000  -0.5964   0.01572   0.00891   0.0489   1.0000   0.6865
  -2.750  -0.5806   0.01578   0.00909   0.0515   1.0000   0.7228
  -2.500  -0.5639   0.01590   0.00931   0.0540   1.0000   0.7585
  -2.250  -0.5451   0.01607   0.00956   0.0561   1.0000   0.7921
  -2.000  -0.5222   0.01631   0.00983   0.0573   1.0000   0.8231
  -1.750  -0.4934   0.01664   0.01017   0.0572   1.0000   0.8522
  -1.500  -0.4373   0.01739   0.01086   0.0517   0.9936   0.8789
  -1.250  -0.3702   0.01830   0.01170   0.0445   0.9881   0.8991
  -1.000  -0.2950   0.01938   0.01270   0.0358   0.9840   0.9155
  -0.750  -0.2258   0.02011   0.01335   0.0278   0.9781   0.9279
  -0.500  -0.1510   0.02070   0.01388   0.0185   0.9726   0.9354
  -0.250  -0.0824   0.02101   0.01415   0.0103   0.9638   0.9452
   0.000   0.0001   0.02116   0.01428   0.0000   0.9548   0.9548
   0.250   0.0824   0.02102   0.01415  -0.0103   0.9453   0.9640
   0.500   0.1510   0.02070   0.01388  -0.0185   0.9354   0.9726
   0.750   0.2261   0.02010   0.01334  -0.0279   0.9279   0.9781
   1.000   0.2952   0.01937   0.01269  -0.0358   0.9154   0.9839
   1.250   0.3702   0.01829   0.01169  -0.0445   0.8990   0.9880
   1.500   0.4375   0.01739   0.01086  -0.0518   0.8792   0.9935
   1.750   0.4935   0.01663   0.01016  -0.0572   0.8521   1.0000
   2.000   0.5221   0.01631   0.00984  -0.0573   0.8232   1.0000
   2.250   0.5450   0.01607   0.00955  -0.0561   0.7919   1.0000
   2.500   0.5637   0.01589   0.00929  -0.0540   0.7579   1.0000
   2.750   0.5805   0.01578   0.00908  -0.0515   0.7225   1.0000
   3.000   0.5963   0.01572   0.00889  -0.0488   0.6862   1.0000
   3.250   0.6097   0.01572   0.00880  -0.0459   0.6468   1.0000
   3.500   0.6234   0.01576   0.00867  -0.0429   0.6055   1.0000
   3.750   0.6360   0.01587   0.00862  -0.0398   0.5604   1.0000
   4.000   0.6485   0.01607   0.00863  -0.0368   0.5147   1.0000
   4.250   0.6607   0.01633   0.00871  -0.0338   0.4681   1.0000
   4.500   0.6727   0.01665   0.00883  -0.0308   0.4219   1.0000
   4.750   0.6843   0.01707   0.00902  -0.0278   0.3789   1.0000
   5.000   0.6956   0.01760   0.00931  -0.0249   0.3394   1.0000
   5.250   0.7066   0.01824   0.00972  -0.0219   0.3012   1.0000
   5.500   0.7165   0.01894   0.01021  -0.0187   0.2599   1.0000
   5.750   0.7253   0.01979   0.01079  -0.0154   0.2180   1.0000
   6.000   0.7359   0.02074   0.01149  -0.0123   0.1906   1.0000
   6.250   0.7500   0.02168   0.01228  -0.0099   0.1736   1.0000
   6.500   0.7668   0.02267   0.01313  -0.0079   0.1629   1.0000
   6.750   0.7853   0.02354   0.01401  -0.0062   0.1547   1.0000
   7.000   0.8054   0.02463   0.01504  -0.0048   0.1481   1.0000
   7.250   0.8243   0.02551   0.01603  -0.0031   0.1421   1.0000
   7.500   0.8455   0.02658   0.01702  -0.0020   0.1372   1.0000
   7.750   0.8669   0.02794   0.01847  -0.0009   0.1337   1.0000
   8.000   0.8854   0.02911   0.01987   0.0009   0.1302   1.0000
   8.250   0.9033   0.03025   0.02114   0.0026   0.1261   1.0000
   8.500   0.9243   0.03171   0.02254   0.0035   0.1223   1.0000
   8.750   0.9383   0.03335   0.02447   0.0058   0.1195   1.0000
   9.000   0.9494   0.03463   0.02607   0.0086   0.1154   1.0000
   9.250   0.9653   0.03567   0.02713   0.0103   0.1105   1.0000
   9.500   0.9767   0.03743   0.02902   0.0125   0.1062   1.0000
   9.750   0.9812   0.03894   0.03091   0.0161   0.1020   1.0000
  10.000   0.9965   0.04002   0.03196   0.0177   0.0970   1.0000
  10.250   1.0016   0.04236   0.03448   0.0205   0.0933   1.0000
  10.500   0.9951   0.04458   0.03716   0.0251   0.0904   1.0000
  10.750   0.9959   0.04652   0.03930   0.0284   0.0868   1.0000
  11.000   1.0154   0.04899   0.04154   0.0285   0.0821   1.0000
  11.250   0.9953   0.05139   0.04441   0.0342   0.0809   1.0000
  11.500   0.9742   0.05437   0.04773   0.0392   0.0801   1.0000
  11.750   0.9467   0.05718   0.05079   0.0446   0.0796   1.0000
  12.000   0.9178   0.06054   0.05438   0.0485   0.0795   1.0000
  12.250   0.8884   0.06461   0.05863   0.0505   0.0797   1.0000
  12.500   0.8577   0.06963   0.06382   0.0506   0.0803   1.0000
  12.750   0.8250   0.07584   0.07015   0.0488   0.0809   1.0000
  13.000   0.7969   0.08286   0.07725   0.0459   0.0816   1.0000
  13.250   0.4916   0.13544   0.13017   0.0179   0.1652   1.0000
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