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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 200,000
Max Cl/Cd: 75.3 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe682-il-200000-n5.txt
Download as CSV file: xf-goe682-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 682 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3551   0.08922   0.08564  -0.0419   1.0000   0.0317
  -9.000  -0.3684   0.08570   0.08219  -0.0416   1.0000   0.0319
  -8.750  -0.3829   0.07727   0.07382  -0.0489   0.9943   0.0328
  -8.500  -0.3647   0.07519   0.07173  -0.0518   0.9885   0.0335
  -8.250  -0.3481   0.07215   0.06869  -0.0563   0.9812   0.0342
  -8.000  -0.3351   0.06540   0.06191  -0.0659   0.9711   0.0346
  -7.750  -0.3217   0.05654   0.05294  -0.0782   0.9611   0.0352
  -7.500  -0.3221   0.03861   0.03432  -0.0950   0.9469   0.0367
  -7.250  -0.3078   0.03095   0.02583  -0.0995   0.9389   0.0380
  -7.000  -0.2884   0.02737   0.02165  -0.1004   0.9302   0.0388
  -6.750  -0.2628   0.02504   0.01880  -0.1013   0.9237   0.0397
  -6.500  -0.2375   0.02327   0.01676  -0.1017   0.9162   0.0407
  -6.250  -0.2081   0.02210   0.01545  -0.1025   0.9107   0.0416
  -6.000  -0.1823   0.02105   0.01421  -0.1025   0.9023   0.0422
  -5.750  -0.1513   0.01999   0.01295  -0.1033   0.8969   0.0431
  -5.500  -0.1261   0.01910   0.01190  -0.1029   0.8874   0.0439
  -5.250  -0.0955   0.01821   0.01081  -0.1035   0.8813   0.0449
  -5.000  -0.0697   0.01749   0.00993  -0.1031   0.8717   0.0460
  -4.750  -0.0398   0.01686   0.00912  -0.1034   0.8646   0.0476
  -4.500  -0.0133   0.01633   0.00845  -0.1030   0.8544   0.0486
  -4.250   0.0139   0.01555   0.00758  -0.1027   0.8441   0.0498
  -4.000   0.0416   0.01495   0.00692  -0.1026   0.8330   0.0512
  -3.750   0.0676   0.01452   0.00644  -0.1021   0.8205   0.0526
  -3.500   0.0942   0.01415   0.00599  -0.1017   0.8098   0.0545
  -3.250   0.1216   0.01379   0.00555  -0.1014   0.8008   0.0567
  -3.000   0.1479   0.01354   0.00522  -0.1009   0.7904   0.0592
  -2.750   0.1741   0.01316   0.00482  -0.1005   0.7811   0.0630
  -2.500   0.2008   0.01291   0.00452  -0.1001   0.7716   0.0671
  -2.250   0.2272   0.01271   0.00425  -0.0997   0.7619   0.0715
  -2.000   0.2539   0.01245   0.00395  -0.0993   0.7532   0.0780
  -1.750   0.2801   0.01227   0.00375  -0.0988   0.7435   0.0874
  -1.500   0.3063   0.01202   0.00358  -0.0984   0.7345   0.1069
  -1.250   0.3322   0.01179   0.00351  -0.0980   0.7251   0.1537
  -1.000   0.3585   0.01166   0.00347  -0.0976   0.7163   0.1962
  -0.750   0.3850   0.01158   0.00340  -0.0972   0.7076   0.2272
  -0.500   0.4110   0.01148   0.00337  -0.0968   0.6982   0.2573
   0.000   0.4623   0.01122   0.00333  -0.0958   0.6801   0.3444
   0.250   0.4851   0.01081   0.00334  -0.0948   0.6700   0.4755
   0.750   0.5724   0.00983   0.00336  -0.1006   0.6441   1.0000
   1.000   0.5966   0.00994   0.00337  -0.0997   0.6317   1.0000
   1.250   0.6207   0.01007   0.00338  -0.0988   0.6188   1.0000
   1.500   0.6448   0.01020   0.00339  -0.0979   0.6050   1.0000
   1.750   0.6690   0.01034   0.00343  -0.0970   0.5923   1.0000
   2.000   0.6934   0.01048   0.00348  -0.0962   0.5802   1.0000
   2.250   0.7179   0.01062   0.00356  -0.0954   0.5679   1.0000
   2.500   0.7422   0.01077   0.00364  -0.0946   0.5549   1.0000
   2.750   0.7663   0.01093   0.00373  -0.0938   0.5416   1.0000
   3.000   0.7905   0.01110   0.00383  -0.0929   0.5286   1.0000
   3.250   0.8144   0.01128   0.00395  -0.0921   0.5151   1.0000
   3.750   0.8615   0.01169   0.00422  -0.0903   0.4857   1.0000
   4.000   0.8847   0.01192   0.00438  -0.0893   0.4708   1.0000
   4.250   0.9079   0.01216   0.00457  -0.0884   0.4567   1.0000
   4.500   0.9311   0.01242   0.00478  -0.0875   0.4434   1.0000
   4.750   0.9540   0.01268   0.00500  -0.0865   0.4303   1.0000
   5.000   0.9766   0.01297   0.00525  -0.0855   0.4172   1.0000
   5.250   0.9989   0.01327   0.00550  -0.0845   0.4033   1.0000
   5.500   1.0209   0.01359   0.00578  -0.0834   0.3886   1.0000
   5.750   1.0426   0.01391   0.00608  -0.0823   0.3733   1.0000
   6.000   1.0641   0.01424   0.00638  -0.0812   0.3582   1.0000
   6.250   1.0852   0.01459   0.00671  -0.0800   0.3426   1.0000
   6.500   1.1058   0.01496   0.00705  -0.0787   0.3269   1.0000
   6.750   1.1256   0.01537   0.00743  -0.0774   0.3109   1.0000
   7.000   1.1445   0.01581   0.00783  -0.0759   0.2949   1.0000
   7.250   1.1627   0.01629   0.00825  -0.0743   0.2809   1.0000
   7.500   1.1812   0.01676   0.00870  -0.0728   0.2693   1.0000
   7.750   1.1999   0.01722   0.00919  -0.0713   0.2599   1.0000
   8.250   1.2349   0.01821   0.01018  -0.0681   0.2423   1.0000
   8.500   1.2497   0.01876   0.01071  -0.0660   0.2331   1.0000
   8.750   1.2644   0.01929   0.01126  -0.0640   0.2233   1.0000
   9.000   1.2796   0.01981   0.01182  -0.0620   0.2146   1.0000
   9.250   1.2929   0.02043   0.01243  -0.0599   0.2057   1.0000
   9.500   1.3084   0.02095   0.01302  -0.0581   0.1961   1.0000
   9.750   1.3215   0.02159   0.01368  -0.0561   0.1860   1.0000
  10.000   1.3338   0.02228   0.01439  -0.0541   0.1728   1.0000
  10.250   1.3460   0.02300   0.01512  -0.0522   0.1569   1.0000
  10.500   1.3567   0.02385   0.01596  -0.0501   0.1391   1.0000
  10.750   1.3632   0.02500   0.01701  -0.0478   0.1160   1.0000
  11.000   1.3642   0.02659   0.01843  -0.0451   0.0912   1.0000
  11.250   1.3648   0.02832   0.02006  -0.0426   0.0736   1.0000
  11.500   1.3662   0.03008   0.02178  -0.0404   0.0566   1.0000
  11.750   1.3642   0.03221   0.02382  -0.0382   0.0403   1.0000
  12.000   1.3635   0.03432   0.02593  -0.0363   0.0320   1.0000
  12.250   1.3635   0.03648   0.02813  -0.0348   0.0279   1.0000
  12.500   1.3652   0.03856   0.03032  -0.0335   0.0254   1.0000
  12.750   1.3649   0.04093   0.03278  -0.0323   0.0235   1.0000
  13.000   1.3624   0.04363   0.03556  -0.0314   0.0221   1.0000
  13.250   1.3625   0.04617   0.03824  -0.0307   0.0210   1.0000
  13.500   1.3615   0.04892   0.04113  -0.0302   0.0200   1.0000
  13.750   1.3587   0.05199   0.04432  -0.0299   0.0194   1.0000
  14.000   1.3538   0.05543   0.04791  -0.0299   0.0187   1.0000
  14.250   1.3474   0.05922   0.05181  -0.0302   0.0181   1.0000
  14.500   1.3394   0.06338   0.05610  -0.0308   0.0177   1.0000
  14.750   1.3308   0.06781   0.06066  -0.0316   0.0174   1.0000
  15.000   1.3248   0.07204   0.06504  -0.0325   0.0171   1.0000
  15.250   1.3184   0.07644   0.06958  -0.0336   0.0168   1.0000
  15.500   1.3110   0.08113   0.07441  -0.0350   0.0165   1.0000
  15.750   1.3041   0.08587   0.07929  -0.0365   0.0162   1.0000
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