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GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 479 AIRFOIL (goe479-il)
Reynolds number: 200,000
Max Cl/Cd: 75.06 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe479-il-200000.txt
Download as CSV file: xf-goe479-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 479 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4028   0.08896   0.08557  -0.0380   1.0000   0.0749
  -8.250  -0.3316   0.08055   0.07747  -0.0311   0.9997   0.0776
  -8.000  -0.4741   0.08099   0.07765  -0.0436   0.9984   0.0755
  -7.750  -0.4519   0.07959   0.07639  -0.0368   0.9980   0.0766
  -7.500  -0.4249   0.07834   0.07514  -0.0348   0.9956   0.0782
  -7.250  -0.3988   0.07450   0.07127  -0.0400   0.9901   0.0812
  -7.000  -0.3828   0.06204   0.05848  -0.0613   0.9771   0.0885
  -6.750  -0.3534   0.06006   0.05656  -0.0621   0.9732   0.0901
  -6.500  -0.3241   0.05728   0.05372  -0.0655   0.9681   0.0938
  -6.250  -0.3021   0.05022   0.04629  -0.0740   0.9586   0.1026
  -6.000  -0.2940   0.03552   0.03036  -0.0787   0.9470   0.0737
  -5.750  -0.2656   0.02968   0.02390  -0.0811   0.9425   0.0688
  -5.500  -0.2403   0.02658   0.02028  -0.0813   0.9343   0.0683
  -5.250  -0.2061   0.02400   0.01720  -0.0828   0.9293   0.0680
  -5.000  -0.1643   0.02227   0.01522  -0.0856   0.9265   0.0692
  -4.750  -0.1312   0.02112   0.01389  -0.0864   0.9184   0.0714
  -4.500  -0.0921   0.01980   0.01233  -0.0882   0.9129   0.0734
  -4.250  -0.0502   0.01866   0.01094  -0.0905   0.9093   0.0751
  -4.000  -0.0236   0.01744   0.00968  -0.0900   0.8989   0.0772
  -3.750   0.0135   0.01659   0.00886  -0.0916   0.8937   0.0813
  -3.500   0.0412   0.01601   0.00822  -0.0912   0.8833   0.0850
  -3.250   0.0754   0.01510   0.00728  -0.0921   0.8769   0.0894
  -3.000   0.1012   0.01461   0.00684  -0.0914   0.8656   0.0951
  -2.750   0.1320   0.01401   0.00622  -0.0916   0.8574   0.1034
  -2.500   0.1588   0.01362   0.00583  -0.0910   0.8464   0.1140
  -2.250   0.1847   0.01313   0.00544  -0.0904   0.8358   0.1322
  -2.000   0.2130   0.01257   0.00504  -0.0902   0.8270   0.1745
  -1.750   0.2363   0.01213   0.00487  -0.0892   0.8152   0.2381
  -1.500   0.2616   0.01172   0.00469  -0.0886   0.8049   0.3108
  -1.250   0.2845   0.01112   0.00455  -0.0875   0.7951   0.4370
  -1.000   0.2996   0.01035   0.00462  -0.0846   0.7843   0.6693
  -0.500   0.4629   0.00982   0.00444  -0.1049   0.7660   1.0000
  -0.250   0.4857   0.00989   0.00436  -0.1038   0.7550   1.0000
   0.000   0.5098   0.00996   0.00427  -0.1028   0.7445   1.0000
   0.250   0.5315   0.01006   0.00428  -0.1015   0.7325   1.0000
   0.500   0.5548   0.01018   0.00428  -0.1004   0.7216   1.0000
   0.750   0.5792   0.01030   0.00426  -0.0995   0.7112   1.0000
   1.000   0.6012   0.01042   0.00433  -0.0982   0.6990   1.0000
   1.250   0.6243   0.01056   0.00437  -0.0971   0.6874   1.0000
   1.500   0.6478   0.01069   0.00438  -0.0960   0.6749   1.0000
   1.750   0.6707   0.01082   0.00440  -0.0947   0.6614   1.0000
   2.000   0.6926   0.01095   0.00448  -0.0933   0.6478   1.0000
   2.250   0.7155   0.01110   0.00457  -0.0922   0.6355   1.0000
   2.500   0.7393   0.01127   0.00465  -0.0911   0.6243   1.0000
   2.750   0.7622   0.01142   0.00474  -0.0900   0.6121   1.0000
   3.000   0.7847   0.01158   0.00488  -0.0888   0.5997   1.0000
   3.250   0.8079   0.01176   0.00500  -0.0877   0.5882   1.0000
   3.500   0.8316   0.01194   0.00510  -0.0867   0.5771   1.0000
   3.750   0.8536   0.01210   0.00527  -0.0854   0.5646   1.0000
   4.000   0.8763   0.01228   0.00542  -0.0842   0.5527   1.0000
   4.250   0.8995   0.01247   0.00556  -0.0832   0.5416   1.0000
   4.500   0.9218   0.01264   0.00570  -0.0819   0.5289   1.0000
   4.750   0.9432   0.01281   0.00585  -0.0805   0.5145   1.0000
   5.000   0.9645   0.01299   0.00601  -0.0791   0.4996   1.0000
   5.250   0.9853   0.01319   0.00616  -0.0776   0.4839   1.0000
   5.500   1.0061   0.01342   0.00635  -0.0762   0.4685   1.0000
   5.750   1.0268   0.01368   0.00658  -0.0747   0.4533   1.0000
   6.000   1.0474   0.01397   0.00683  -0.0733   0.4385   1.0000
   6.250   1.0671   0.01426   0.00709  -0.0717   0.4223   1.0000
   6.500   1.0866   0.01457   0.00737  -0.0701   0.4060   1.0000
   6.750   1.1059   0.01489   0.00769  -0.0685   0.3905   1.0000
   7.000   1.1246   0.01521   0.00800  -0.0668   0.3741   1.0000
   7.250   1.1422   0.01555   0.00832  -0.0649   0.3558   1.0000
   7.500   1.1590   0.01591   0.00867  -0.0629   0.3370   1.0000
   7.750   1.1743   0.01632   0.00903  -0.0607   0.3166   1.0000
   8.000   1.1887   0.01677   0.00943  -0.0584   0.2934   1.0000
   8.250   1.2004   0.01733   0.00990  -0.0556   0.2706   1.0000
   8.500   1.2098   0.01795   0.01043  -0.0526   0.2450   1.0000
   8.750   1.2161   0.01871   0.01107  -0.0490   0.2172   1.0000
   9.000   1.2183   0.01973   0.01188  -0.0451   0.1792   1.0000
   9.250   1.2143   0.02124   0.01300  -0.0407   0.1224   1.0000
   9.500   1.2112   0.02286   0.01433  -0.0367   0.0908   1.0000
   9.750   1.2138   0.02421   0.01561  -0.0336   0.0805   1.0000
  10.000   1.2181   0.02549   0.01692  -0.0308   0.0757   1.0000
  10.250   1.2234   0.02677   0.01826  -0.0284   0.0724   1.0000
  10.500   1.2260   0.02828   0.01980  -0.0259   0.0698   1.0000
  10.750   1.2246   0.03015   0.02168  -0.0234   0.0676   1.0000
  11.000   1.2305   0.03161   0.02324  -0.0216   0.0660   1.0000
  11.250   1.2355   0.03322   0.02493  -0.0199   0.0645   1.0000
  11.500   1.2399   0.03493   0.02671  -0.0184   0.0629   1.0000
  11.750   1.2440   0.03676   0.02858  -0.0170   0.0615   1.0000
  12.000   1.2486   0.03861   0.03046  -0.0156   0.0603   1.0000
  12.250   1.2545   0.04046   0.03228  -0.0142   0.0591   1.0000
  12.500   1.2647   0.04207   0.03390  -0.0129   0.0579   1.0000
  12.750   1.2745   0.04362   0.03557  -0.0120   0.0568   1.0000
  13.000   1.2857   0.04512   0.03715  -0.0110   0.0557   1.0000
  13.250   1.2977   0.04662   0.03873  -0.0101   0.0546   1.0000
  13.500   1.3098   0.04816   0.04032  -0.0092   0.0534   1.0000
  13.750   1.3230   0.04968   0.04185  -0.0084   0.0520   1.0000
  14.000   1.3490   0.05084   0.04295  -0.0076   0.0505   1.0000
  14.250   1.3678   0.05270   0.04492  -0.0068   0.0495   1.0000
  14.500   1.3722   0.05481   0.04723  -0.0060   0.0489   1.0000
  14.750   1.3759   0.05711   0.04972  -0.0053   0.0482   1.0000
  15.000   1.3789   0.05953   0.05233  -0.0047   0.0474   1.0000
  15.250   1.3811   0.06207   0.05504  -0.0042   0.0466   1.0000
  15.500   1.3839   0.06467   0.05778  -0.0039   0.0457   1.0000
  15.750   1.3884   0.06728   0.06052  -0.0035   0.0450   1.0000
  16.000   1.3908   0.07007   0.06343  -0.0034   0.0443   1.0000
  16.250   1.3958   0.07290   0.06635  -0.0032   0.0436   1.0000
  16.500   1.4101   0.07698   0.07053  -0.0030   0.0424   1.0000
  16.750   1.3921   0.08118   0.07496  -0.0036   0.0423   1.0000
  17.000   1.3736   0.08583   0.07985  -0.0046   0.0421   1.0000
  17.250   1.3541   0.09102   0.08529  -0.0063   0.0420   1.0000
  17.500   1.3323   0.09679   0.09130  -0.0086   0.0419   1.0000
  17.750   1.3109   0.10303   0.09776  -0.0114   0.0418   1.0000
  18.000   1.2881   0.10993   0.10488  -0.0149   0.0418   1.0000
  18.250   1.2643   0.11743   0.11260  -0.0190   0.0418   1.0000
  18.500   1.2400   0.12553   0.12091  -0.0236   0.0420   1.0000
  18.750   1.2146   0.13435   0.12991  -0.0290   0.0422   1.0000
  19.000   1.1895   0.14375   0.13947  -0.0347   0.0424   1.0000
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