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GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 510 AIRFOIL (goe510-il)
Reynolds number: 500,000
Max Cl/Cd: 84.79 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe510-il-500000.txt
Download as CSV file: xf-goe510-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 510 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0738   0.08906   0.08659  -0.0922   0.9660   0.0421
  -9.000  -0.0596   0.08623   0.08376  -0.0945   0.9622   0.0430
  -8.750  -0.0437   0.08285   0.08037  -0.0984   0.9598   0.0440
  -8.500  -0.0487   0.07306   0.07057  -0.1163   0.9560   0.0468
  -8.250  -0.0613   0.06778   0.06528  -0.1186   0.9458   0.0471
  -8.000  -0.0420   0.06497   0.06246  -0.1202   0.9439   0.0474
  -7.750  -0.0189   0.06234   0.05982  -0.1231   0.9421   0.0478
  -7.500  -0.0120   0.06024   0.05771  -0.1227   0.9335   0.0481
  -7.250   0.0101   0.05751   0.05494  -0.1260   0.9296   0.0488
  -7.000   0.0375   0.05412   0.05150  -0.1313   0.9268   0.0499
  -6.750   0.0118   0.03988   0.03678  -0.1386   0.9112   0.0548
  -6.500   0.0234   0.03894   0.03584  -0.1364   0.9007   0.0551
  -6.250   0.0528   0.03775   0.03461  -0.1381   0.8955   0.0556
  -6.000   0.0662   0.03663   0.03343  -0.1364   0.8846   0.0561
  -5.750   0.0895   0.03471   0.03140  -0.1374   0.8768   0.0571
  -5.500   0.0985   0.03090   0.02733  -0.1362   0.8655   0.0595
  -5.250   0.0710   0.02190   0.01713  -0.1284   0.8515   0.0522
  -5.000   0.0869   0.01964   0.01452  -0.1264   0.8420   0.0509
  -4.750   0.1076   0.01818   0.01275  -0.1251   0.8322   0.0508
  -4.500   0.1273   0.01715   0.01150  -0.1234   0.8216   0.0510
  -4.250   0.1522   0.01629   0.01041  -0.1228   0.8116   0.0514
  -4.000   0.1736   0.01561   0.00955  -0.1213   0.7999   0.0520
  -3.750   0.1959   0.01515   0.00893  -0.1200   0.7885   0.0528
  -3.500   0.2202   0.01483   0.00843  -0.1190   0.7775   0.0535
  -3.250   0.2420   0.01450   0.00797  -0.1175   0.7652   0.0539
  -3.000   0.2636   0.01388   0.00721  -0.1161   0.7527   0.0543
  -2.750   0.2860   0.01303   0.00627  -0.1149   0.7397   0.0552
  -2.500   0.3081   0.01262   0.00580  -0.1136   0.7262   0.0561
  -2.250   0.3295   0.01235   0.00545  -0.1121   0.7123   0.0569
  -2.000   0.3503   0.01213   0.00518  -0.1105   0.6984   0.0580
  -1.750   0.3712   0.01196   0.00494  -0.1089   0.6847   0.0593
  -1.500   0.3917   0.01181   0.00471  -0.1072   0.6710   0.0604
  -1.250   0.4118   0.01168   0.00449  -0.1054   0.6576   0.0612
  -1.000   0.4318   0.01160   0.00432  -0.1036   0.6445   0.0620
  -0.750   0.4512   0.01143   0.00410  -0.1017   0.6316   0.0629
  -0.500   0.4692   0.01117   0.00380  -0.0995   0.6191   0.0645
  -0.250   0.4864   0.01109   0.00367  -0.0971   0.6058   0.0659
   0.000   0.5022   0.01104   0.00357  -0.0945   0.5922   0.0680
   0.250   0.5181   0.01099   0.00348  -0.0918   0.5779   0.0696
   0.500   0.5337   0.01097   0.00340  -0.0891   0.5625   0.0710
   0.750   0.5492   0.01100   0.00335  -0.0864   0.5462   0.0723
   1.000   0.5634   0.01098   0.00327  -0.0834   0.5292   0.0754
   1.250   0.5786   0.01104   0.00326  -0.0807   0.5126   0.0788
   1.500   0.5949   0.01113   0.00328  -0.0783   0.4976   0.0833
   1.750   0.6105   0.01116   0.00333  -0.0757   0.4846   0.1029
   2.000   0.6239   0.01109   0.00352  -0.0728   0.4736   0.2105
   2.250   0.6431   0.01120   0.00367  -0.0711   0.4640   0.2471
   2.750   0.6827   0.01149   0.00395  -0.0678   0.4482   0.2833
   3.000   0.7023   0.01166   0.00408  -0.0662   0.4413   0.2975
   3.250   0.7227   0.01180   0.00422  -0.0648   0.4355   0.3120
   3.500   0.7435   0.01190   0.00434  -0.0634   0.4298   0.3237
   3.750   0.7628   0.01205   0.00448  -0.0617   0.4241   0.3366
   4.000   0.7829   0.01218   0.00462  -0.0602   0.4190   0.3526
   4.250   0.8030   0.01221   0.00475  -0.0588   0.4143   0.3787
   4.500   0.8068   0.01163   0.00485  -0.0540   0.4104   0.6739
   4.750   1.0121   0.01222   0.00609  -0.0926   0.3974   0.9971
   5.000   1.0564   0.01248   0.00630  -0.0964   0.3917   1.0000
   5.250   1.0690   0.01270   0.00645  -0.0935   0.3875   1.0000
   5.500   1.0831   0.01282   0.00659  -0.0908   0.3838   1.0000
   5.750   1.0972   0.01294   0.00672  -0.0882   0.3798   1.0000
   6.000   1.1104   0.01310   0.00687  -0.0854   0.3755   1.0000
   6.250   1.1234   0.01333   0.00705  -0.0826   0.3710   1.0000
   6.500   1.1386   0.01350   0.00723  -0.0802   0.3671   1.0000
   6.750   1.1541   0.01365   0.00740  -0.0779   0.3630   1.0000
   7.000   1.1687   0.01385   0.00760  -0.0755   0.3585   1.0000
   7.500   1.1982   0.01429   0.00803  -0.0708   0.3477   1.0000
   7.750   1.2124   0.01452   0.00825  -0.0685   0.3413   1.0000
   8.000   1.2265   0.01486   0.00855  -0.0661   0.3359   1.0000
   8.250   1.2438   0.01505   0.00879  -0.0644   0.3296   1.0000
   8.500   1.2568   0.01540   0.00909  -0.0620   0.3218   1.0000
   8.750   1.2731   0.01568   0.00939  -0.0602   0.3141   1.0000
   9.000   1.2869   0.01608   0.00976  -0.0580   0.3062   1.0000
   9.250   1.3028   0.01643   0.01013  -0.0563   0.2986   1.0000
   9.500   1.3169   0.01688   0.01055  -0.0543   0.2906   1.0000
   9.750   1.3322   0.01730   0.01098  -0.0525   0.2829   1.0000
  10.000   1.3453   0.01784   0.01149  -0.0505   0.2746   1.0000
  10.250   1.3596   0.01835   0.01200  -0.0487   0.2650   1.0000
  10.500   1.3708   0.01903   0.01264  -0.0466   0.2556   1.0000
  10.750   1.3826   0.01971   0.01329  -0.0446   0.2443   1.0000
  11.000   1.3931   0.02049   0.01404  -0.0426   0.2317   1.0000
  11.250   1.4019   0.02139   0.01489  -0.0404   0.2185   1.0000
  11.500   1.4086   0.02246   0.01589  -0.0381   0.2030   1.0000
  11.750   1.4099   0.02390   0.01720  -0.0353   0.1828   1.0000
  12.000   1.4062   0.02575   0.01888  -0.0322   0.1549   1.0000
  12.250   1.3961   0.02813   0.02106  -0.0288   0.1241   1.0000
  12.500   1.3798   0.03115   0.02389  -0.0253   0.0943   1.0000
  12.750   1.3633   0.03441   0.02700  -0.0223   0.0674   1.0000
  13.000   1.3387   0.03866   0.03112  -0.0193   0.0324   1.0000
  13.250   1.3332   0.04148   0.03399  -0.0179   0.0268   1.0000
  13.500   1.3319   0.04403   0.03662  -0.0168   0.0247   1.0000
  13.750   1.3328   0.04646   0.03913  -0.0160   0.0238   1.0000
  14.000   1.3317   0.04916   0.04193  -0.0152   0.0227   1.0000
  14.250   1.3318   0.05180   0.04468  -0.0147   0.0221   1.0000
  14.500   1.3306   0.05465   0.04762  -0.0142   0.0215   1.0000
  14.750   1.3288   0.05763   0.05071  -0.0139   0.0211   1.0000
  15.000   1.3226   0.06122   0.05441  -0.0137   0.0206   1.0000
  15.250   1.3151   0.06505   0.05834  -0.0137   0.0201   1.0000
  15.500   1.3039   0.06945   0.06286  -0.0139   0.0197   1.0000
  15.750   1.2940   0.07381   0.06734  -0.0142   0.0195   1.0000
  16.000   1.2873   0.07783   0.07146  -0.0146   0.0192   1.0000
  16.250   1.2801   0.08198   0.07571  -0.0152   0.0189   1.0000
  16.500   1.2723   0.08624   0.08007  -0.0158   0.0187   1.0000
  16.750   1.2635   0.09071   0.08465  -0.0166   0.0185   1.0000
  17.000   1.2548   0.09523   0.08927  -0.0174   0.0182   1.0000
  17.250   1.2455   0.09983   0.09397  -0.0184   0.0179   1.0000
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