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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.92 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe385-il-1000000.txt
Download as CSV file: xf-goe385-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2879   0.09802   0.09654  -0.0244   1.0000   0.0131
  -9.750  -0.2824   0.09511   0.09365  -0.0250   1.0000   0.0133
  -9.250  -0.3922   0.09817   0.09663  -0.0181   1.0000   0.0130
  -9.000  -0.3847   0.09546   0.09393  -0.0191   1.0000   0.0132
  -8.750  -0.3779   0.09257   0.09105  -0.0205   1.0000   0.0134
  -8.500  -0.3714   0.08960   0.08810  -0.0222   1.0000   0.0136
  -8.250  -0.3659   0.08643   0.08495  -0.0242   1.0000   0.0140
  -8.000  -0.3619   0.08314   0.08168  -0.0264   1.0000   0.0144
  -7.750  -0.3518   0.07885   0.07740  -0.0317   0.9876   0.0151
  -7.500  -0.3326   0.07011   0.06860  -0.0467   0.9683   0.0161
  -7.250  -0.3205   0.06470   0.06312  -0.0519   0.9504   0.0161
  -5.500  -0.1963   0.03453   0.03152  -0.0661   0.8150   0.0203
  -5.250  -0.1795   0.02603   0.02240  -0.0668   0.8057   0.0206
  -5.000  -0.1557   0.02653   0.02295  -0.0674   0.7938   0.0214
  -4.750  -0.1306   0.02606   0.02242  -0.0676   0.7812   0.0221
  -4.500  -0.1001   0.02581   0.02191  -0.0670   0.7663   0.0255
  -4.250  -0.0743   0.02343   0.01916  -0.0668   0.7490   0.0257
  -4.000  -0.0523   0.01814   0.01333  -0.0669   0.7283   0.0267
  -3.750  -0.0259   0.01762   0.01271  -0.0671   0.6992   0.0274
  -3.500   0.0009   0.01707   0.01199  -0.0671   0.6749   0.0285
  -3.250   0.0288   0.01661   0.01134  -0.0671   0.6587   0.0308
  -3.000   0.0585   0.01777   0.01235  -0.0668   0.6463   0.0326
  -2.500   0.1131   0.01313   0.00720  -0.0668   0.6295   0.0310
  -2.250   0.1415   0.01221   0.00614  -0.0668   0.6218   0.0311
  -2.000   0.1698   0.01160   0.00540  -0.0667   0.6150   0.0313
  -1.750   0.1982   0.01099   0.00472  -0.0668   0.6083   0.0314
  -1.500   0.2264   0.01052   0.00417  -0.0668   0.6020   0.0315
  -1.250   0.2549   0.01007   0.00369  -0.0668   0.5964   0.0316
  -1.000   0.2832   0.00972   0.00330  -0.0669   0.5906   0.0318
  -0.750   0.3118   0.00961   0.00315  -0.0670   0.5847   0.0324
  -0.500   0.3402   0.00931   0.00284  -0.0670   0.5783   0.0329
  -0.250   0.3683   0.00885   0.00231  -0.0671   0.5710   0.0336
   0.000   0.3969   0.00857   0.00202  -0.0673   0.5635   0.0345
   0.500   0.4543   0.00833   0.00172  -0.0676   0.5494   0.0361
   0.750   0.4829   0.00827   0.00163  -0.0677   0.5418   0.0372
   1.000   0.5117   0.00820   0.00156  -0.0679   0.5337   0.0389
   1.250   0.5403   0.00818   0.00150  -0.0680   0.5242   0.0408
   1.500   0.5689   0.00817   0.00145  -0.0682   0.5129   0.0430
   1.750   0.5974   0.00815   0.00142  -0.0683   0.5000   0.0534
   2.000   0.6211   0.00600   0.00157  -0.0681   0.4865   1.0000
   2.250   0.6490   0.00614   0.00161  -0.0681   0.4689   1.0000
   2.500   0.6768   0.00631   0.00166  -0.0682   0.4482   1.0000
   2.750   0.7043   0.00651   0.00174  -0.0682   0.4250   1.0000
   3.000   0.7319   0.00671   0.00183  -0.0683   0.4043   1.0000
   3.500   0.7864   0.00719   0.00208  -0.0683   0.3595   1.0000
   3.750   0.8139   0.00739   0.00220  -0.0684   0.3445   1.0000
   4.000   0.8414   0.00759   0.00234  -0.0684   0.3324   1.0000
   4.250   0.8688   0.00779   0.00248  -0.0685   0.3211   1.0000
   4.500   0.8964   0.00795   0.00261  -0.0686   0.3116   1.0000
   4.750   0.9239   0.00814   0.00276  -0.0686   0.3025   1.0000
   5.250   0.9785   0.00852   0.00307  -0.0687   0.2828   1.0000
   5.500   1.0056   0.00872   0.00323  -0.0688   0.2732   1.0000
   5.750   1.0325   0.00895   0.00342  -0.0688   0.2626   1.0000
   6.000   1.0594   0.00916   0.00360  -0.0688   0.2512   1.0000
   6.250   1.0862   0.00937   0.00378  -0.0688   0.2409   1.0000
   6.500   1.1125   0.00964   0.00400  -0.0687   0.2268   1.0000
   6.750   1.1387   0.00992   0.00423  -0.0686   0.2132   1.0000
   7.000   1.1642   0.01027   0.00450  -0.0685   0.1952   1.0000
   7.250   1.1867   0.01095   0.00494  -0.0680   0.1528   1.0000
   7.500   1.2077   0.01177   0.00554  -0.0672   0.1170   1.0000
   7.750   1.2310   0.01231   0.00600  -0.0668   0.1007   1.0000
   8.000   1.2510   0.01320   0.00664  -0.0659   0.0605   1.0000
   8.250   1.2722   0.01392   0.00728  -0.0651   0.0415   1.0000
   8.500   1.2900   0.01497   0.00814  -0.0639   0.0167   1.0000
   8.750   1.3125   0.01547   0.00870  -0.0632   0.0149   1.0000
   9.000   1.3335   0.01610   0.00936  -0.0624   0.0133   1.0000
   9.250   1.3541   0.01674   0.01007  -0.0615   0.0123   1.0000
   9.500   1.3752   0.01728   0.01067  -0.0607   0.0118   1.0000
   9.750   1.3951   0.01790   0.01135  -0.0597   0.0112   1.0000
  10.000   1.4136   0.01858   0.01209  -0.0585   0.0106   1.0000
  10.250   1.4300   0.01938   0.01295  -0.0571   0.0101   1.0000
  10.500   1.4391   0.02066   0.01434  -0.0546   0.0094   1.0000
  10.750   1.4510   0.02147   0.01524  -0.0525   0.0092   1.0000
  11.000   1.4627   0.02223   0.01605  -0.0504   0.0089   1.0000
  11.250   1.4722   0.02317   0.01707  -0.0482   0.0087   1.0000
  11.500   1.4809   0.02424   0.01822  -0.0461   0.0084   1.0000
  11.750   1.4882   0.02549   0.01955  -0.0442   0.0081   1.0000
  12.000   1.4947   0.02689   0.02103  -0.0424   0.0079   1.0000
  12.250   1.5000   0.02850   0.02272  -0.0409   0.0077   1.0000
  12.500   1.5042   0.03036   0.02467  -0.0397   0.0075   1.0000
  12.750   1.5062   0.03255   0.02695  -0.0387   0.0073   1.0000
  13.000   1.5047   0.03524   0.02973  -0.0378   0.0072   1.0000
  13.250   1.4982   0.03860   0.03321  -0.0372   0.0070   1.0000
  13.500   1.4874   0.04266   0.03739  -0.0369   0.0069   1.0000
  13.750   1.4731   0.04730   0.04217  -0.0369   0.0068   1.0000
  14.000   1.4671   0.05106   0.04603  -0.0371   0.0067   1.0000
  14.250   1.4662   0.05427   0.04934  -0.0374   0.0067   1.0000
  14.500   1.4640   0.05767   0.05284  -0.0378   0.0066   1.0000
  14.750   1.4609   0.06128   0.05655  -0.0383   0.0065   1.0000
  15.000   1.4570   0.06504   0.06041  -0.0389   0.0064   1.0000
  15.250   1.4524   0.06902   0.06448  -0.0397   0.0064   1.0000
  15.500   1.4479   0.07309   0.06866  -0.0407   0.0063   1.0000
  15.750   1.4419   0.07741   0.07308  -0.0417   0.0061   1.0000
  16.000   1.4359   0.08182   0.07758  -0.0429   0.0061   1.0000
  16.250   1.4300   0.08632   0.08218  -0.0441   0.0060   1.0000
  16.500   1.4236   0.09095   0.08691  -0.0455   0.0059   1.0000
  16.750   1.4165   0.09569   0.09173  -0.0469   0.0058   1.0000
  17.000   1.4097   0.10046   0.09660  -0.0485   0.0057   1.0000
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