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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 50,000
Max Cl/Cd: 39.21 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802a-il-50000-n5.txt
Download as CSV file: xf-goe802a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2646   0.11718   0.11055  -0.0331   1.0000   0.0637
  -9.000  -0.2732   0.11625   0.10973  -0.0314   1.0000   0.0638
  -8.750  -0.2827   0.11518   0.10878  -0.0294   1.0000   0.0640
  -8.500  -0.2852   0.11260   0.10627  -0.0273   1.0000   0.0645
  -8.250  -0.2929   0.11100   0.10476  -0.0250   1.0000   0.0650
  -8.000  -0.3019   0.10963   0.10347  -0.0227   1.0000   0.0655
  -7.750  -0.3090   0.10807   0.10200  -0.0212   1.0000   0.0661
  -7.500  -0.3150   0.10644   0.10045  -0.0200   1.0000   0.0668
  -7.250  -0.3189   0.10466   0.09874  -0.0196   0.9997   0.0676
  -7.000  -0.2939   0.10100   0.09503  -0.0274   0.9916   0.0692
  -6.750  -0.2710   0.09709   0.09110  -0.0332   0.9839   0.0700
  -6.500  -0.2491   0.09310   0.08708  -0.0374   0.9771   0.0717
  -6.250  -0.2236   0.08942   0.08333  -0.0433   0.9692   0.0732
  -6.000  -0.1962   0.08596   0.07979  -0.0498   0.9609   0.0743
  -5.750  -0.1675   0.08231   0.07605  -0.0558   0.9530   0.0748
  -5.500  -0.1419   0.07858   0.07226  -0.0599   0.9462   0.0761
  -5.250  -0.1155   0.07538   0.06897  -0.0644   0.9372   0.0778
  -5.000  -0.0775   0.07183   0.06526  -0.0713   0.9311   0.0791
  -4.750  -0.0555   0.06891   0.06227  -0.0738   0.9216   0.0807
  -4.500  -0.0184   0.06580   0.05896  -0.0795   0.9145   0.0819
  -4.250   0.0166   0.06269   0.05567  -0.0842   0.9078   0.0825
  -4.000   0.0439   0.06004   0.05289  -0.0868   0.8983   0.0835
  -3.750   0.0864   0.05718   0.04978  -0.0923   0.8928   0.0844
  -3.500   0.1150   0.05503   0.04743  -0.0945   0.8830   0.0848
  -3.250   0.1515   0.05241   0.04460  -0.0981   0.8761   0.0860
  -3.000   0.1932   0.05020   0.04208  -0.1022   0.8703   0.0866
  -2.750   0.2183   0.04831   0.04004  -0.1031   0.8593   0.0871
  -2.250   0.2852   0.04485   0.03605  -0.1069   0.8423   0.0877
  -2.000   0.3245   0.04319   0.03407  -0.1094   0.8357   0.0879
  -1.750   0.3522   0.04209   0.03271  -0.1099   0.8249   0.0880
  -1.500   0.3879   0.04039   0.03076  -0.1116   0.8173   0.0882
  -1.250   0.4164   0.03917   0.02933  -0.1121   0.8068   0.0887
  -1.000   0.4511   0.03814   0.02797  -0.1131   0.7982   0.0892
  -0.750   0.4795   0.03728   0.02688  -0.1132   0.7874   0.0894
  -0.500   0.5129   0.03609   0.02545  -0.1140   0.7786   0.0895
  -0.250   0.5398   0.03531   0.02449  -0.1138   0.7671   0.0896
   0.000   0.5733   0.03430   0.02325  -0.1143   0.7586   0.0897
   0.250   0.5985   0.03375   0.02253  -0.1138   0.7463   0.0898
   0.500   0.6324   0.03284   0.02139  -0.1143   0.7382   0.0901
   0.750   0.6561   0.03261   0.02099  -0.1134   0.7252   0.0909
   1.000   0.6905   0.03169   0.01984  -0.1139   0.7178   0.0928
   1.250   0.7127   0.03147   0.01951  -0.1130   0.7044   0.0943
   1.500   0.7414   0.03085   0.01874  -0.1128   0.6946   0.0959
   1.750   0.7687   0.03046   0.01816  -0.1123   0.6835   0.0988
   2.000   0.7956   0.02994   0.01747  -0.1118   0.6725   0.1052
   2.250   0.8247   0.02822   0.01578  -0.1117   0.6632   0.1186
   2.500   0.8492   0.02775   0.01537  -0.1114   0.6516   0.1277
   2.750   0.8795   0.02727   0.01483  -0.1115   0.6425   0.1356
   3.000   0.9030   0.02726   0.01497  -0.1111   0.6301   0.1513
   3.500   0.9506   0.02614   0.01521  -0.1094   0.6092   1.0000
   3.750   0.9778   0.02636   0.01526  -0.1090   0.5996   1.0000
   4.000   1.0012   0.02680   0.01562  -0.1084   0.5884   1.0000
   4.250   1.0262   0.02718   0.01591  -0.1079   0.5782   1.0000
   4.500   1.0510   0.02756   0.01621  -0.1073   0.5679   1.0000
   4.750   1.0744   0.02808   0.01670  -0.1068   0.5578   1.0000
   5.000   1.0995   0.02849   0.01708  -0.1063   0.5482   1.0000
   5.250   1.1218   0.02909   0.01768  -0.1056   0.5381   1.0000
   5.500   1.1464   0.02954   0.01811  -0.1051   0.5287   1.0000
   5.750   1.1681   0.03021   0.01880  -0.1044   0.5190   1.0000
   6.000   1.1918   0.03071   0.01933  -0.1038   0.5094   1.0000
   6.250   1.2117   0.03136   0.02002  -0.1028   0.4982   1.0000
   6.500   1.2375   0.03156   0.02014  -0.1022   0.4873   1.0000
   6.750   1.2523   0.03238   0.02107  -0.1005   0.4744   1.0000
   7.000   1.2749   0.03275   0.02144  -0.0996   0.4634   1.0000
   7.250   1.2924   0.03342   0.02219  -0.0982   0.4520   1.0000
   7.500   1.3105   0.03413   0.02296  -0.0970   0.4415   1.0000
   7.750   1.3309   0.03466   0.02353  -0.0959   0.4313   1.0000
   8.000   1.3450   0.03558   0.02461  -0.0942   0.4206   1.0000
   8.250   1.3675   0.03594   0.02496  -0.0933   0.4106   1.0000
   8.500   1.3766   0.03710   0.02631  -0.0912   0.3994   1.0000
   8.750   1.3989   0.03746   0.02665  -0.0902   0.3895   1.0000
   9.000   1.4053   0.03872   0.02810  -0.0878   0.3781   1.0000
   9.250   1.4211   0.03944   0.02891  -0.0862   0.3678   1.0000
   9.500   1.4307   0.04048   0.03007  -0.0841   0.3569   1.0000
   9.750   1.4381   0.04160   0.03130  -0.0816   0.3464   1.0000
  10.000   1.4507   0.04238   0.03212  -0.0797   0.3355   1.0000
  10.250   1.4495   0.04412   0.03403  -0.0768   0.3245   1.0000
  10.500   1.4656   0.04472   0.03463  -0.0752   0.3138   1.0000
  10.750   1.4583   0.04704   0.03718  -0.0723   0.3028   1.0000
  11.000   1.4650   0.04836   0.03852  -0.0704   0.2922   1.0000
  11.250   1.4626   0.05040   0.04068  -0.0681   0.2811   1.0000
  11.500   1.4586   0.05275   0.04315  -0.0661   0.2706   1.0000
  11.750   1.4628   0.05427   0.04466  -0.0644   0.2601   1.0000
  12.000   1.4508   0.05779   0.04838  -0.0629   0.2504   1.0000
  12.250   1.4594   0.05899   0.04954  -0.0615   0.2413   1.0000
  12.500   1.4433   0.06342   0.05425  -0.0606   0.2328   1.0000
  12.750   1.4501   0.06503   0.05586  -0.0595   0.2250   1.0000
  13.000   1.4373   0.06946   0.06049  -0.0591   0.2179   1.0000
  13.250   1.4344   0.07262   0.06376  -0.0586   0.2112   1.0000
  13.500   1.4430   0.07427   0.06542  -0.0577   0.2054   1.0000
  13.750   1.4195   0.08070   0.07213  -0.0584   0.1997   1.0000
  14.000   1.4166   0.08415   0.07569  -0.0583   0.1941   1.0000
  14.250   1.4343   0.08445   0.07596  -0.0570   0.1889   1.0000
  14.500   1.3895   0.09496   0.08681  -0.0600   0.1841   1.0000
  14.750   1.3591   0.10371   0.09573  -0.0628   0.1788   1.0000
  15.000   1.3977   0.09990   0.09190  -0.0597   0.1739   1.0000
  15.250   1.3377   0.11481   0.10701  -0.0659   0.1696   1.0000
  15.500   1.2492   0.13816   0.13041  -0.0777   0.1603   1.0000
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