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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 100,000
Max Cl/Cd: 52.22 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe509-il-100000-n5.txt
Download as CSV file: xf-goe509-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3016   0.10941   0.10477  -0.0342   1.0000   0.0527
  -9.000  -0.3132   0.10751   0.10298  -0.0343   1.0000   0.0532
  -8.750  -0.3236   0.10557   0.10112  -0.0336   1.0000   0.0534
  -8.500  -0.3251   0.10253   0.09815  -0.0359   0.9972   0.0535
  -8.000  -0.3036   0.08863   0.08420  -0.0461   0.9847   0.0350
  -7.750  -0.2901   0.08458   0.08013  -0.0497   0.9766   0.0345
  -7.500  -0.2782   0.07883   0.07435  -0.0567   0.9658   0.0349
  -7.250  -0.2664   0.07317   0.06862  -0.0624   0.9552   0.0351
  -7.000  -0.2536   0.06715   0.06249  -0.0678   0.9452   0.0353
  -6.500  -0.2303   0.05696   0.05203  -0.0728   0.9244   0.0352
  -6.250  -0.2221   0.05085   0.04565  -0.0741   0.9128   0.0353
  -6.000  -0.2005   0.04820   0.04291  -0.0753   0.9063   0.0364
  -5.750  -0.1862   0.04667   0.04129  -0.0744   0.8952   0.0381
  -5.500  -0.1736   0.04242   0.03671  -0.0740   0.8851   0.0397
  -5.250  -0.1563   0.03728   0.03099  -0.0740   0.8787   0.0408
  -5.000  -0.1447   0.03347   0.02656  -0.0717   0.8687   0.0421
  -4.750  -0.1196   0.03051   0.02300  -0.0716   0.8637   0.0449
  -4.500  -0.0982   0.02928   0.02163  -0.0706   0.8546   0.0470
  -4.250  -0.0663   0.02725   0.01915  -0.0712   0.8498   0.0498
  -4.000  -0.0420   0.02578   0.01716  -0.0701   0.8406   0.0534
  -3.750  -0.0070   0.02400   0.01511  -0.0713   0.8351   0.0559
  -3.500   0.0207   0.02315   0.01413  -0.0711   0.8256   0.0596
  -3.250   0.0577   0.02201   0.01269  -0.0724   0.8199   0.0637
  -3.000   0.0866   0.02121   0.01162  -0.0722   0.8112   0.0663
  -2.750   0.1218   0.02021   0.01064  -0.0736   0.8046   0.0712
  -2.500   0.1503   0.01958   0.00991  -0.0734   0.7949   0.0752
  -2.250   0.1859   0.01890   0.00905  -0.0745   0.7872   0.0798
  -2.000   0.2111   0.01838   0.00856  -0.0738   0.7763   0.0858
  -1.750   0.2419   0.01793   0.00800  -0.0741   0.7670   0.0939
  -1.500   0.2698   0.01746   0.00754  -0.0739   0.7566   0.1030
  -1.250   0.2978   0.01707   0.00718  -0.0737   0.7454   0.1202
  -1.000   0.3307   0.01654   0.00692  -0.0745   0.7343   0.1732
  -0.750   0.3590   0.01636   0.00694  -0.0744   0.7217   0.2751
  -0.500   0.3839   0.01631   0.00686  -0.0736   0.7077   0.3196
  -0.250   0.4092   0.01619   0.00674  -0.0729   0.6936   0.3533
   0.000   0.4340   0.01601   0.00659  -0.0722   0.6792   0.3933
   0.250   0.4564   0.01560   0.00639  -0.0710   0.6642   0.4582
   0.500   0.6273   0.01493   0.00657  -0.1002   0.6365   0.9966
   0.750   0.6571   0.01504   0.00649  -0.1006   0.6170   1.0000
   1.000   0.6783   0.01518   0.00645  -0.0991   0.5988   1.0000
   1.250   0.6992   0.01533   0.00643  -0.0976   0.5810   1.0000
   1.500   0.7199   0.01551   0.00644  -0.0961   0.5638   1.0000
   1.750   0.7404   0.01571   0.00648  -0.0946   0.5480   1.0000
   2.000   0.7609   0.01593   0.00654  -0.0931   0.5335   1.0000
   2.250   0.7812   0.01616   0.00663  -0.0916   0.5202   1.0000
   2.500   0.8016   0.01640   0.00673  -0.0901   0.5080   1.0000
   2.750   0.8219   0.01667   0.00684  -0.0886   0.4968   1.0000
   3.000   0.8423   0.01694   0.00702  -0.0871   0.4862   1.0000
   3.250   0.8628   0.01723   0.00721  -0.0857   0.4766   1.0000
   3.500   0.8833   0.01753   0.00740  -0.0843   0.4675   1.0000
   3.750   0.9035   0.01783   0.00764  -0.0829   0.4584   1.0000
   4.000   0.9243   0.01817   0.00787  -0.0815   0.4501   1.0000
   4.250   0.9447   0.01846   0.00816  -0.0802   0.4425   1.0000
   4.500   0.9661   0.01879   0.00845  -0.0790   0.4362   1.0000
   4.750   0.9878   0.01913   0.00877  -0.0779   0.4305   1.0000
   5.000   1.0083   0.01945   0.00913  -0.0766   0.4242   1.0000
   5.250   1.0299   0.01981   0.00945  -0.0755   0.4183   1.0000
   5.500   1.0500   0.02016   0.00983  -0.0742   0.4119   1.0000
   5.750   1.0698   0.02051   0.01023  -0.0728   0.4051   1.0000
   6.000   1.0908   0.02089   0.01059  -0.0716   0.3990   1.0000
   6.250   1.1084   0.02123   0.01105  -0.0698   0.3917   1.0000
   6.500   1.1278   0.02160   0.01144  -0.0683   0.3849   1.0000
   6.750   1.1452   0.02196   0.01190  -0.0665   0.3777   1.0000
   7.000   1.1626   0.02233   0.01233  -0.0647   0.3705   1.0000
   7.250   1.1796   0.02270   0.01278  -0.0629   0.3631   1.0000
   7.500   1.1943   0.02306   0.01325  -0.0606   0.3544   1.0000
   7.750   1.2086   0.02343   0.01370  -0.0583   0.3455   1.0000
   8.000   1.2214   0.02379   0.01411  -0.0557   0.3361   1.0000
   8.250   1.2328   0.02419   0.01463  -0.0529   0.3251   1.0000
   8.500   1.2433   0.02460   0.01509  -0.0500   0.3151   1.0000
   8.750   1.2517   0.02501   0.01557  -0.0467   0.3053   1.0000
   9.000   1.2606   0.02549   0.01613  -0.0436   0.2951   1.0000
   9.250   1.2681   0.02602   0.01669  -0.0404   0.2847   1.0000
   9.500   1.2745   0.02661   0.01727  -0.0371   0.2742   1.0000
   9.750   1.2815   0.02730   0.01800  -0.0342   0.2630   1.0000
  10.000   1.2897   0.02805   0.01882  -0.0315   0.2542   1.0000
  10.250   1.2961   0.02888   0.01965  -0.0288   0.2461   1.0000
  10.500   1.3048   0.02975   0.02062  -0.0265   0.2382   1.0000
  11.000   1.3197   0.03169   0.02271  -0.0219   0.2255   1.0000
  11.250   1.3253   0.03280   0.02387  -0.0196   0.2194   1.0000
  11.500   1.3308   0.03400   0.02520  -0.0175   0.2122   1.0000
  11.750   1.3333   0.03539   0.02664  -0.0153   0.2050   1.0000
  12.000   1.3379   0.03679   0.02816  -0.0135   0.1986   1.0000
  12.250   1.3413   0.03832   0.02980  -0.0117   0.1928   1.0000
  12.500   1.3429   0.04003   0.03159  -0.0100   0.1869   1.0000
  12.750   1.3445   0.04186   0.03360  -0.0086   0.1801   1.0000
  13.000   1.3426   0.04401   0.03579  -0.0071   0.1739   1.0000
  13.250   1.3414   0.04629   0.03829  -0.0060   0.1660   1.0000
  13.500   1.3345   0.04914   0.04119  -0.0050   0.1580   1.0000
  13.750   1.3288   0.05220   0.04445  -0.0044   0.1472   1.0000
  14.000   1.3218   0.05554   0.04796  -0.0041   0.1359   1.0000
  14.250   1.3120   0.05943   0.05199  -0.0041   0.1158   1.0000
  14.500   1.2921   0.06468   0.05717  -0.0047   0.0958   1.0000
  14.750   1.2709   0.07048   0.06291  -0.0058   0.0876   1.0000
  15.000   1.2510   0.07641   0.06883  -0.0071   0.0792   1.0000
  15.500   1.2180   0.08784   0.08040  -0.0099   0.0629   1.0000
  15.750   1.2022   0.09365   0.08629  -0.0115   0.0570   1.0000
  16.000   1.1847   0.09983   0.09253  -0.0134   0.0527   1.0000
  16.250   1.1681   0.10602   0.09879  -0.0154   0.0504   1.0000
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