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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 200,000
Max Cl/Cd: 79.12 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe379-il-200000-n5.txt
Download as CSV file: xf-goe379-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2726   0.09589   0.09266  -0.0272   1.0000   0.0164
  -7.500  -0.2737   0.09390   0.09073  -0.0265   1.0000   0.0165
  -7.250  -0.2804   0.09280   0.08972  -0.0251   1.0000   0.0173
  -7.000  -0.2661   0.08977   0.08672  -0.0297   0.9916   0.0177
  -6.750  -0.2380   0.08621   0.08315  -0.0392   0.9805   0.0181
  -6.500  -0.2126   0.08229   0.07920  -0.0461   0.9712   0.0182
  -6.250  -0.1847   0.07813   0.07501  -0.0530   0.9626   0.0183
  -6.000  -0.1556   0.07387   0.07071  -0.0593   0.9549   0.0184
  -5.750  -0.1286   0.06976   0.06655  -0.0646   0.9450   0.0184
  -5.500  -0.0994   0.06557   0.06229  -0.0700   0.9360   0.0185
  -5.250  -0.0502   0.04004   0.03693  -0.0699   0.8913   0.0202
  -5.000  -0.0344   0.03690   0.03374  -0.0712   0.8800   0.0219
  -4.750  -0.0158   0.03352   0.03027  -0.0737   0.8687   0.0228
  -4.500   0.0042   0.03005   0.02669  -0.0762   0.8579   0.0230
  -4.000   0.0529   0.04183   0.03792  -0.0889   0.8721   0.0163
  -3.750   0.0787   0.03848   0.03439  -0.0905   0.8605   0.0150
  -3.500   0.1056   0.03517   0.03087  -0.0917   0.8494   0.0142
  -3.250   0.1328   0.03184   0.02725  -0.0924   0.8384   0.0135
  -3.000   0.1595   0.02853   0.02363  -0.0926   0.8263   0.0132
  -2.750   0.1858   0.02523   0.01995  -0.0921   0.8136   0.0130
  -2.500   0.2115   0.02231   0.01661  -0.0913   0.8000   0.0144
  -2.250   0.2369   0.01887   0.01261  -0.0900   0.7872   0.0156
  -2.000   0.2624   0.01581   0.00885  -0.0886   0.7748   0.0163
  -1.750   0.2885   0.01407   0.00660  -0.0877   0.7629   0.0176
  -1.500   0.3143   0.01309   0.00537  -0.0869   0.7510   0.0217
  -1.250   0.3402   0.01247   0.00454  -0.0862   0.7388   0.0274
  -1.000   0.3663   0.01224   0.00423  -0.0856   0.7261   0.0406
  -0.750   0.3923   0.01217   0.00403  -0.0851   0.7129   0.0543
  -0.500   0.4183   0.01216   0.00389  -0.0846   0.6996   0.0668
  -0.250   0.4437   0.01195   0.00354  -0.0839   0.6862   0.0722
   0.000   0.4689   0.01176   0.00323  -0.0833   0.6723   0.0768
   0.250   0.4940   0.01164   0.00303  -0.0826   0.6578   0.0840
   0.500   0.5191   0.01154   0.00285  -0.0820   0.6432   0.0916
   0.750   0.5441   0.01147   0.00270  -0.0814   0.6290   0.1006
   1.000   0.5690   0.01141   0.00259  -0.0807   0.6149   0.1144
   1.250   0.5936   0.01134   0.00255  -0.0801   0.6006   0.1477
   1.750   0.6961   0.00991   0.00257  -0.0910   0.5673   1.0000
   2.000   0.7205   0.01008   0.00262  -0.0903   0.5545   1.0000
   2.250   0.7448   0.01027   0.00268  -0.0896   0.5420   1.0000
   2.750   0.7929   0.01067   0.00289  -0.0881   0.5145   1.0000
   3.000   0.8167   0.01088   0.00302  -0.0873   0.4998   1.0000
   3.500   0.8643   0.01130   0.00335  -0.0858   0.4722   1.0000
   3.750   0.8881   0.01152   0.00353  -0.0850   0.4586   1.0000
   4.000   0.9117   0.01174   0.00373  -0.0843   0.4452   1.0000
   4.250   0.9353   0.01197   0.00398  -0.0835   0.4326   1.0000
   4.500   0.9587   0.01221   0.00422  -0.0827   0.4200   1.0000
   4.750   0.9821   0.01247   0.00448  -0.0819   0.4088   1.0000
   5.000   1.0052   0.01274   0.00476  -0.0811   0.3984   1.0000
   5.250   1.0285   0.01300   0.00510  -0.0803   0.3877   1.0000
   5.500   1.0512   0.01329   0.00544  -0.0794   0.3750   1.0000
   5.750   1.0705   0.01374   0.00576  -0.0780   0.3440   1.0000
   6.000   1.0894   0.01424   0.00615  -0.0766   0.3118   1.0000
   6.250   1.1055   0.01497   0.00661  -0.0747   0.2507   1.0000
   6.500   1.1106   0.01679   0.00768  -0.0715   0.1306   1.0000
   6.750   1.1108   0.01919   0.00938  -0.0675   0.0177   1.0000
   7.000   1.1284   0.01993   0.01033  -0.0658   0.0145   1.0000
   7.250   1.1437   0.02085   0.01142  -0.0637   0.0118   1.0000
   7.500   1.1538   0.02216   0.01301  -0.0609   0.0102   1.0000
   7.750   1.1646   0.02328   0.01431  -0.0583   0.0097   1.0000
   8.000   1.1727   0.02447   0.01567  -0.0554   0.0093   1.0000
   8.250   1.1778   0.02566   0.01697  -0.0520   0.0087   1.0000
   8.500   1.1827   0.02680   0.01821  -0.0488   0.0078   1.0000
   8.750   1.1853   0.02820   0.01976  -0.0456   0.0074   1.0000
   9.000   1.1858   0.02988   0.02153  -0.0424   0.0069   1.0000
   9.250   1.1865   0.03175   0.02347  -0.0396   0.0067   1.0000
   9.500   1.1882   0.03378   0.02556  -0.0371   0.0065   1.0000
   9.750   1.1925   0.03609   0.02791  -0.0348   0.0064   1.0000
  10.000   1.2050   0.03845   0.03031  -0.0330   0.0062   1.0000
  10.250   1.2187   0.04046   0.03247  -0.0314   0.0061   1.0000
  10.500   1.2341   0.04275   0.03493  -0.0301   0.0061   1.0000
  10.750   1.2433   0.04505   0.03750  -0.0283   0.0059   1.0000
  11.000   1.2506   0.04749   0.04018  -0.0267   0.0058   1.0000
  11.250   1.2519   0.04969   0.04266  -0.0249   0.0053   1.0000
  11.500   1.2529   0.05237   0.04558  -0.0234   0.0050   1.0000
  11.750   1.2513   0.05519   0.04861  -0.0222   0.0047   1.0000
  12.000   1.2474   0.05854   0.05220  -0.0211   0.0046   1.0000
  12.250   1.2424   0.06210   0.05601  -0.0203   0.0047   1.0000
  12.500   1.2340   0.06608   0.06024  -0.0199   0.0048   1.0000
  12.750   1.2237   0.07033   0.06472  -0.0199   0.0047   1.0000
  13.000   1.2117   0.07489   0.06950  -0.0205   0.0047   1.0000
  13.250   1.1990   0.07980   0.07463  -0.0216   0.0047   1.0000
  13.500   1.1853   0.08511   0.08015  -0.0232   0.0048   1.0000
  13.750   1.1700   0.09085   0.08609  -0.0254   0.0048   1.0000
  14.000   1.1556   0.09682   0.09224  -0.0281   0.0048   1.0000
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