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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 50,000
Max Cl/Cd: 37.5 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe682-il-50000-n5.txt
Download as CSV file: xf-goe682-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3347   0.10803   0.10115  -0.0363   1.0000   0.1448
  -8.500  -0.3482   0.10643   0.09968  -0.0359   1.0000   0.1451
  -8.250  -0.3609   0.10467   0.09805  -0.0347   1.0000   0.1452
  -8.000  -0.3398   0.09521   0.08846  -0.0356   1.0000   0.0968
  -7.750  -0.3914   0.09193   0.08543  -0.0387   1.0000   0.0865
  -7.500  -0.3863   0.08959   0.08313  -0.0353   1.0000   0.0855
  -7.250  -0.3929   0.08712   0.08074  -0.0341   1.0000   0.0849
  -7.000  -0.4011   0.08449   0.07817  -0.0334   1.0000   0.0846
  -6.750  -0.4091   0.08162   0.07535  -0.0334   1.0000   0.0846
  -6.500  -0.4145   0.07862   0.07238  -0.0335   1.0000   0.0843
  -6.250  -0.3978   0.07357   0.06721  -0.0392   0.9938   0.0839
  -6.000  -0.3738   0.06820   0.06167  -0.0456   0.9856   0.0827
  -5.750  -0.3494   0.06255   0.05580  -0.0522   0.9770   0.0816
  -5.500  -0.3240   0.05709   0.05004  -0.0581   0.9685   0.0810
  -5.250  -0.2965   0.05185   0.04436  -0.0637   0.9605   0.0828
  -5.000  -0.2660   0.04686   0.03879  -0.0687   0.9533   0.0843
  -4.750  -0.2391   0.04309   0.03450  -0.0714   0.9450   0.0848
  -4.500  -0.2066   0.03971   0.03049  -0.0742   0.9387   0.0855
  -4.250  -0.1774   0.03706   0.02723  -0.0758   0.9307   0.0865
  -4.000  -0.1467   0.03552   0.02561  -0.0773   0.9239   0.0896
  -3.750  -0.1164   0.03423   0.02411  -0.0785   0.9160   0.0933
  -3.500  -0.0836   0.03266   0.02211  -0.0798   0.9091   0.0966
  -3.250  -0.0518   0.03122   0.02026  -0.0807   0.9013   0.0994
  -3.000  -0.0169   0.03005   0.01887  -0.0821   0.8948   0.1030
  -2.500   0.0515   0.02848   0.01703  -0.0845   0.8797   0.1178
  -2.000   0.1204   0.02723   0.01563  -0.0866   0.8640   0.1401
  -1.750   0.1488   0.02678   0.01516  -0.0866   0.8540   0.1570
  -1.500   0.1851   0.02619   0.01461  -0.0879   0.8471   0.1886
  -1.250   0.2136   0.02569   0.01428  -0.0880   0.8376   0.2348
  -1.000   0.2456   0.02513   0.01394  -0.0887   0.8299   0.3015
  -0.750   0.2738   0.02457   0.01372  -0.0888   0.8210   0.3815
  -0.500   0.3287   0.02247   0.01337  -0.0924   0.8173   1.0000
  -0.250   0.3518   0.02272   0.01330  -0.0916   0.8059   1.0000
   0.000   0.3826   0.02283   0.01311  -0.0919   0.7973   1.0000
   0.500   0.4376   0.02317   0.01302  -0.0914   0.7779   1.0000
   0.750   0.4716   0.02317   0.01283  -0.0920   0.7704   1.0000
   1.000   0.4942   0.02348   0.01300  -0.0911   0.7591   1.0000
   1.250   0.5237   0.02360   0.01297  -0.0910   0.7502   1.0000
   1.500   0.5518   0.02374   0.01301  -0.0908   0.7406   1.0000
   1.750   0.5758   0.02402   0.01320  -0.0900   0.7296   1.0000
   2.000   0.6105   0.02395   0.01302  -0.0906   0.7222   1.0000
   2.250   0.6318   0.02432   0.01334  -0.0894   0.7100   1.0000
   2.500   0.6564   0.02457   0.01354  -0.0886   0.6986   1.0000
   2.750   0.6868   0.02454   0.01343  -0.0884   0.6880   1.0000
   3.000   0.7162   0.02444   0.01328  -0.0878   0.6753   1.0000
   3.250   0.7407   0.02450   0.01329  -0.0867   0.6605   1.0000
   3.500   0.7652   0.02458   0.01332  -0.0855   0.6456   1.0000
   3.750   0.7892   0.02472   0.01345  -0.0844   0.6313   1.0000
   4.000   0.8133   0.02492   0.01364  -0.0834   0.6177   1.0000
   4.250   0.8380   0.02511   0.01382  -0.0825   0.6046   1.0000
   4.500   0.8636   0.02527   0.01398  -0.0816   0.5917   1.0000
   4.750   0.8897   0.02542   0.01412  -0.0809   0.5787   1.0000
   5.000   0.9110   0.02576   0.01449  -0.0796   0.5642   1.0000
   5.250   0.9325   0.02609   0.01487  -0.0783   0.5495   1.0000
   5.500   0.9541   0.02642   0.01523  -0.0770   0.5346   1.0000
   5.750   0.9757   0.02676   0.01561  -0.0757   0.5197   1.0000
   6.000   0.9972   0.02711   0.01599  -0.0744   0.5046   1.0000
   6.250   1.0187   0.02748   0.01641  -0.0732   0.4893   1.0000
   6.500   1.0402   0.02789   0.01684  -0.0719   0.4740   1.0000
   6.750   1.0614   0.02834   0.01732  -0.0706   0.4587   1.0000
   7.000   1.0823   0.02886   0.01788  -0.0694   0.4436   1.0000
   7.250   1.1030   0.02944   0.01850  -0.0681   0.4288   1.0000
   7.500   1.1236   0.03008   0.01918  -0.0670   0.4148   1.0000
   7.750   1.1444   0.03075   0.01988  -0.0658   0.4014   1.0000
   8.000   1.1662   0.03141   0.02059  -0.0648   0.3889   1.0000
   8.250   1.1840   0.03228   0.02158  -0.0634   0.3765   1.0000
   8.500   1.2011   0.03323   0.02265  -0.0621   0.3650   1.0000
   8.750   1.2209   0.03407   0.02358  -0.0609   0.3547   1.0000
   9.000   1.2402   0.03493   0.02453  -0.0598   0.3446   1.0000
   9.250   1.2540   0.03604   0.02585  -0.0581   0.3346   1.0000
   9.500   1.2713   0.03690   0.02679  -0.0567   0.3246   1.0000
   9.750   1.2856   0.03776   0.02774  -0.0549   0.3139   1.0000
  10.000   1.2923   0.03893   0.02909  -0.0524   0.3034   1.0000
  10.250   1.3044   0.03987   0.03012  -0.0504   0.2937   1.0000
  10.500   1.3155   0.04090   0.03130  -0.0484   0.2843   1.0000
  10.750   1.3214   0.04230   0.03290  -0.0461   0.2755   1.0000
  11.000   1.3383   0.04313   0.03377  -0.0447   0.2663   1.0000
  11.250   1.3355   0.04498   0.03589  -0.0419   0.2575   1.0000
  11.500   1.3402   0.04630   0.03730  -0.0397   0.2472   1.0000
  11.750   1.3404   0.04754   0.03854  -0.0372   0.2349   1.0000
  12.000   1.3281   0.04985   0.04103  -0.0347   0.2235   1.0000
  12.250   1.3158   0.05242   0.04371  -0.0327   0.2118   1.0000
  12.500   1.3049   0.05508   0.04643  -0.0312   0.1998   1.0000
  12.750   1.2933   0.05808   0.04947  -0.0303   0.1875   1.0000
  13.000   1.2801   0.06175   0.05332  -0.0300   0.1758   1.0000
  13.250   1.2670   0.06597   0.05777  -0.0303   0.1648   1.0000
  13.500   1.2555   0.07022   0.06218  -0.0308   0.1538   1.0000
  13.750   1.2443   0.07466   0.06674  -0.0317   0.1426   1.0000
  14.000   1.2321   0.07945   0.07163  -0.0329   0.1308   1.0000
  14.250   1.2204   0.08437   0.07658  -0.0343   0.1196   1.0000
  14.500   1.2086   0.08955   0.08179  -0.0359   0.1089   1.0000
  14.750   1.1961   0.09511   0.08736  -0.0378   0.0992   1.0000
  15.000   1.1848   0.10054   0.09274  -0.0396   0.0908   1.0000
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