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GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 693 AIRFOIL (goe693-il)
Reynolds number: 50,000
Max Cl/Cd: 32.28 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe693-il-50000.txt
Download as CSV file: xf-goe693-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 693 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3524   0.10902   0.10186  -0.0293   1.0000   0.2608
  -8.500  -0.3438   0.10520   0.09807  -0.0284   1.0000   0.2670
  -8.250  -0.3546   0.10391   0.09690  -0.0272   1.0000   0.2772
  -8.000  -0.3430   0.10022   0.09324  -0.0257   1.0000   0.2864
  -7.750  -0.3747   0.10041   0.09364  -0.0235   1.0000   0.2947
  -7.500  -0.3563   0.09644   0.08966  -0.0217   1.0000   0.3080
  -7.250  -0.3632   0.09426   0.08760  -0.0192   1.0000   0.3170
  -7.000  -0.3897   0.09400   0.08751  -0.0151   1.0000   0.3268
  -6.750  -0.3807   0.09083   0.08439  -0.0127   1.0000   0.3378
  -6.500  -0.4320   0.09191   0.08572  -0.0074   1.0000   0.3444
  -6.250  -0.4183   0.08860   0.08242  -0.0043   1.0000   0.3576
  -6.000  -0.4268   0.08661   0.08053  -0.0009   1.0000   0.3686
  -5.750  -0.4488   0.08537   0.07941   0.0025   1.0000   0.3813
  -5.250  -0.4631   0.08159   0.07577   0.0095   1.0000   0.4149
  -5.000  -0.4614   0.07958   0.07379   0.0136   1.0000   0.4378
  -4.500  -0.4540   0.05895   0.05196  -0.0281   1.0000   0.2305
  -4.250  -0.4255   0.05152   0.04373  -0.0341   1.0000   0.1981
  -4.000  -0.4040   0.04820   0.04011  -0.0351   1.0000   0.1932
  -3.750  -0.3808   0.04508   0.03657  -0.0364   1.0000   0.1922
  -3.500  -0.3555   0.04241   0.03328  -0.0378   1.0000   0.1954
  -3.250  -0.3317   0.04018   0.03071  -0.0384   1.0000   0.1990
  -3.000  -0.3094   0.03869   0.02905  -0.0384   1.0000   0.2054
  -2.750  -0.2840   0.03717   0.02706  -0.0390   1.0000   0.2150
  -2.500  -0.2610   0.03607   0.02581  -0.0390   1.0000   0.2252
  -2.250  -0.2378   0.03512   0.02472  -0.0391   1.0000   0.2387
  -2.000  -0.2140   0.03430   0.02373  -0.0392   1.0000   0.2534
  -1.750  -0.1904   0.03368   0.02300  -0.0392   1.0000   0.2707
  -1.500  -0.1672   0.03321   0.02243  -0.0392   1.0000   0.2897
  -1.250  -0.1439   0.03287   0.02199  -0.0392   1.0000   0.3103
  -1.000  -0.1205   0.03262   0.02177  -0.0391   1.0000   0.3331
  -0.750  -0.0954   0.03252   0.02164  -0.0394   1.0000   0.3611
  -0.500  -0.0697   0.03237   0.02167  -0.0398   1.0000   0.3976
  -0.250  -0.0417   0.03201   0.02183  -0.0405   1.0000   0.4680
   0.000  -0.0234   0.03011   0.02157  -0.0379   0.9979   1.0000
   0.250   0.0300   0.03154   0.02227  -0.0438   0.9854   1.0000
   0.500   0.0799   0.03286   0.02320  -0.0491   0.9715   1.0000
   0.750   0.1261   0.03403   0.02408  -0.0536   0.9569   1.0000
   1.000   0.1675   0.03506   0.02489  -0.0571   0.9423   1.0000
   1.250   0.2050   0.03600   0.02566  -0.0599   0.9278   1.0000
   1.500   0.2399   0.03691   0.02644  -0.0621   0.9138   1.0000
   1.750   0.2741   0.03782   0.02724  -0.0642   0.8998   1.0000
   2.000   0.3081   0.03872   0.02805  -0.0661   0.8856   1.0000
   2.250   0.3418   0.03961   0.02887  -0.0679   0.8713   1.0000
   2.500   0.3752   0.04048   0.02970  -0.0696   0.8569   1.0000
   2.750   0.4084   0.04133   0.03051  -0.0711   0.8421   1.0000
   3.000   0.4412   0.04217   0.03133  -0.0725   0.8272   1.0000
   3.250   0.4736   0.04299   0.03215  -0.0737   0.8122   1.0000
   3.500   0.5062   0.04379   0.03295  -0.0749   0.7973   1.0000
   3.750   0.5415   0.04451   0.03370  -0.0763   0.7831   1.0000
   4.000   0.5733   0.04524   0.03447  -0.0771   0.7683   1.0000
   4.250   0.5977   0.04618   0.03544  -0.0770   0.7530   1.0000
   4.500   0.6202   0.04721   0.03651  -0.0767   0.7378   1.0000
   4.750   0.6447   0.04811   0.03747  -0.0764   0.7223   1.0000
   5.000   0.6706   0.04884   0.03826  -0.0761   0.7067   1.0000
   5.250   0.6975   0.04943   0.03891  -0.0757   0.6910   1.0000
   5.500   0.7292   0.04954   0.03911  -0.0754   0.6749   1.0000
   5.750   0.7647   0.04914   0.03881  -0.0749   0.6586   1.0000
   6.000   0.7973   0.04882   0.03860  -0.0741   0.6429   1.0000
   6.250   0.8238   0.04896   0.03884  -0.0731   0.6278   1.0000
   6.500   0.8458   0.04950   0.03948  -0.0718   0.6130   1.0000
   6.750   0.8681   0.04999   0.04010  -0.0705   0.5985   1.0000
   7.000   0.8916   0.05036   0.04060  -0.0692   0.5842   1.0000
   7.250   0.9235   0.04984   0.04023  -0.0680   0.5699   1.0000
   7.500   0.9658   0.04829   0.03889  -0.0672   0.5551   1.0000
   7.750   1.0104   0.04650   0.03728  -0.0664   0.5389   1.0000
   8.000   1.0577   0.04451   0.03547  -0.0659   0.5216   1.0000
   8.250   1.1402   0.03946   0.03051  -0.0675   0.4993   1.0000
   8.500   1.1616   0.03925   0.03036  -0.0651   0.4740   1.0000
   8.750   1.1964   0.03840   0.02949  -0.0639   0.4482   1.0000
   9.000   1.2314   0.03815   0.02915  -0.0633   0.4241   1.0000
   9.250   1.2499   0.03919   0.03024  -0.0615   0.4029   1.0000
   9.500   1.2682   0.04033   0.03145  -0.0597   0.3825   1.0000
   9.750   1.2939   0.04132   0.03242  -0.0588   0.3628   1.0000
  10.000   1.3167   0.04256   0.03365  -0.0576   0.3432   1.0000
  10.250   1.3249   0.04424   0.03549  -0.0548   0.3245   1.0000
  10.500   1.3359   0.04511   0.03638  -0.0521   0.3022   1.0000
  10.750   1.3452   0.04540   0.03655  -0.0490   0.2783   1.0000
  11.000   1.3449   0.04626   0.03745  -0.0450   0.2582   1.0000
  11.250   1.3549   0.04664   0.03759  -0.0422   0.2362   1.0000
  11.500   1.3483   0.04819   0.03924  -0.0379   0.2190   1.0000
  11.750   1.3419   0.04980   0.04084  -0.0336   0.2012   1.0000
  12.000   1.3478   0.05175   0.04242  -0.0309   0.1771   1.0000
  12.250   1.3427   0.05476   0.04549  -0.0276   0.1603   1.0000
  12.500   1.3425   0.05795   0.04870  -0.0251   0.1461   1.0000
  12.750   1.3485   0.06084   0.05154  -0.0232   0.1341   1.0000
  13.000   1.3270   0.06451   0.05565  -0.0198   0.1306   1.0000
  13.250   1.3254   0.06760   0.05886  -0.0180   0.1239   1.0000
  13.500   1.3193   0.07148   0.06290  -0.0163   0.1198   1.0000
  13.750   1.2938   0.07635   0.06813  -0.0147   0.1188   1.0000
  14.000   1.2657   0.08192   0.07401  -0.0141   0.1184   1.0000
  14.250   1.2342   0.08839   0.08076  -0.0146   0.1187   1.0000
  14.500   1.1999   0.09591   0.08850  -0.0163   0.1195   1.0000
  14.750   1.1650   0.10443   0.09720  -0.0193   0.1206   1.0000
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