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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 50,000
Max Cl/Cd: 42.59 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe403-il-50000.txt
Download as CSV file: xf-goe403-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 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  -0.3560   0.11216   0.10531  -0.0214   1.0000   0.1283
  -8.500  -0.3599   0.11116   0.10442  -0.0230   1.0000   0.1318
  -8.250  -0.3717   0.11145   0.10487  -0.0249   1.0000   0.1329
  -8.000  -0.3466   0.10369   0.09705  -0.0227   1.0000   0.1394
  -7.750  -0.3486   0.10192   0.09539  -0.0233   1.0000   0.1444
  -7.500  -0.3617   0.10194   0.09559  -0.0246   1.0000   0.1464
  -7.250  -0.3466   0.09633   0.08999  -0.0227   1.0000   0.1515
  -7.000  -0.3482   0.09435   0.08812  -0.0230   1.0000   0.1581
  -6.750  -0.3574   0.09444   0.08836  -0.0280   1.0000   0.1607
  -6.500  -0.3444   0.08894   0.08289  -0.0231   1.0000   0.1713
  -6.250  -0.3452   0.08659   0.08065  -0.0246   1.0000   0.1768
  -6.000  -0.3431   0.08447   0.07861  -0.0252   1.0000   0.1874
  -5.500  -0.3383   0.07888   0.07318  -0.0253   1.0000   0.2038
  -5.250  -0.3347   0.07637   0.07067  -0.0246   1.0000   0.2151
  -5.000  -0.3314   0.07308   0.06745  -0.0220   1.0000   0.2234
  -4.750  -0.3283   0.07048   0.06489  -0.0219   1.0000   0.2352
  -4.500  -0.3239   0.06788   0.06233  -0.0215   1.0000   0.2489
  -4.250  -0.3187   0.06527   0.05974  -0.0207   1.0000   0.2657
  -4.000  -0.3120   0.06268   0.05716  -0.0210   1.0000   0.2881
  -3.750  -0.3079   0.06008   0.05461  -0.0187   1.0000   0.3164
  -3.000  -0.3075   0.05269   0.04747  -0.0050   1.0000   0.4437
  -2.750  -0.3127   0.05033   0.04523   0.0020   1.0000   0.4980
  -2.500  -0.3172   0.04796   0.04297   0.0086   1.0000   0.5512
  -2.250  -0.3193   0.04546   0.04056   0.0148   1.0000   0.5945
  -2.000  -0.0675   0.03536   0.02708  -0.0544   1.0000   0.1893
  -1.750  -0.0379   0.03289   0.02417  -0.0556   1.0000   0.1783
  -1.500  -0.0118   0.03128   0.02217  -0.0562   1.0000   0.1798
  -1.250   0.0130   0.03016   0.02062  -0.0565   1.0000   0.1869
  -1.000   0.0373   0.02906   0.01912  -0.0567   1.0000   0.1872
  -0.750   0.0591   0.02824   0.01801  -0.0567   1.0000   0.1904
  -0.500   0.0789   0.02773   0.01729  -0.0564   1.0000   0.1975
  -0.250   0.1237   0.02727   0.01655  -0.0604   0.9905   0.2216
   0.000   0.1807   0.02666   0.01583  -0.0661   0.9761   0.2765
   0.250   0.2339   0.02534   0.01532  -0.0713   0.9626   0.4300
   0.500   0.2879   0.02425   0.01470  -0.0759   0.9460   1.0000
   0.750   0.3402   0.02499   0.01502  -0.0811   0.9289   1.0000
   1.000   0.3817   0.02563   0.01541  -0.0843   0.9104   1.0000
   1.250   0.4244   0.02621   0.01580  -0.0876   0.8930   1.0000
   1.500   0.4681   0.02671   0.01617  -0.0908   0.8768   1.0000
   1.750   0.5118   0.02715   0.01653  -0.0939   0.8616   1.0000
   2.000   0.5543   0.02755   0.01692  -0.0966   0.8470   1.0000
   2.250   0.5942   0.02793   0.01729  -0.0986   0.8326   1.0000
   2.500   0.6301   0.02836   0.01772  -0.0999   0.8185   1.0000
   2.750   0.6609   0.02891   0.01831  -0.1004   0.8039   1.0000
   3.000   0.6904   0.02949   0.01900  -0.1007   0.7898   1.0000
   3.250   0.7193   0.03009   0.01967  -0.1008   0.7760   1.0000
   3.500   0.7502   0.03059   0.02028  -0.1010   0.7632   1.0000
   3.750   0.7760   0.03128   0.02108  -0.1006   0.7496   1.0000
   4.000   0.8004   0.03205   0.02199  -0.1001   0.7361   1.0000
   4.250   0.8243   0.03284   0.02300  -0.0995   0.7227   1.0000
   4.500   0.8477   0.03366   0.02400  -0.0987   0.7093   1.0000
   4.750   0.8713   0.03445   0.02499  -0.0979   0.6959   1.0000
   5.000   0.8986   0.03487   0.02565  -0.0970   0.6818   1.0000
   5.250   0.9585   0.02813   0.01909  -0.0898   0.6274   1.0000
   5.500   0.9878   0.02690   0.01801  -0.0865   0.5986   1.0000
   5.750   1.0075   0.02484   0.01582  -0.0803   0.5409   1.0000
   6.000   1.0179   0.02405   0.01488  -0.0746   0.4760   1.0000
   6.250   1.0261   0.02409   0.01482  -0.0697   0.4038   1.0000
   6.500   1.0267   0.02544   0.01518  -0.0649   0.2217   1.0000
   6.750   1.0254   0.02891   0.01739  -0.0619   0.1069   1.0000
   7.000   1.0345   0.03113   0.01958  -0.0595   0.0936   1.0000
   7.250   1.0429   0.03318   0.02170  -0.0570   0.0867   1.0000
   7.500   1.0501   0.03523   0.02385  -0.0543   0.0818   1.0000
   7.750   1.0594   0.03715   0.02589  -0.0519   0.0770   1.0000
   8.000   1.0723   0.03932   0.02806  -0.0497   0.0731   1.0000
   8.250   1.1128   0.04167   0.03040  -0.0492   0.0716   1.0000
   8.500   1.1649   0.04487   0.03371  -0.0502   0.0715   1.0000
   8.750   1.2037   0.04848   0.03760  -0.0504   0.0725   1.0000
   9.000   1.2251   0.05111   0.04098  -0.0485   0.0748   1.0000
   9.250   1.2396   0.05489   0.04548  -0.0463   0.0780   1.0000
   9.500   1.2517   0.05921   0.05029  -0.0445   0.0805   1.0000
   9.750   1.2607   0.06378   0.05523  -0.0429   0.0823   1.0000
  10.000   1.2708   0.06897   0.06066  -0.0417   0.0839   1.0000
  10.250   1.2588   0.07209   0.06443  -0.0386   0.0860   1.0000
  10.500   1.2310   0.07603   0.06892  -0.0356   0.0885   1.0000
  10.750   1.2058   0.08012   0.07330  -0.0333   0.0902   1.0000
  11.000   1.1799   0.08470   0.07808  -0.0325   0.0917   1.0000
  11.250   1.1554   0.08998   0.08352  -0.0332   0.0931   1.0000
  11.500   1.1352   0.09591   0.08957  -0.0350   0.0946   1.0000
  11.750   1.1316   0.10197   0.09571  -0.0362   0.0972   1.0000
  12.000   1.0837   0.11074   0.10459  -0.0435   0.0979   1.0000
  12.250   1.0422   0.12244   0.11619  -0.0532   0.0987   1.0000
  12.500   1.0061   0.13662   0.13025  -0.0640   0.1026   1.0000
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