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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 100,000
Max Cl/Cd: 62.07 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe371-il-100000-n5.txt
Download as CSV file: xf-goe371-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3143   0.09631   0.09162  -0.0296   1.0000   0.0375
  -7.500  -0.3227   0.09505   0.09048  -0.0288   1.0000   0.0378
  -7.250  -0.3300   0.09366   0.08920  -0.0292   1.0000   0.0382
  -7.000  -0.3341   0.09194   0.08757  -0.0299   1.0000   0.0384
  -6.750  -0.3371   0.09002   0.08572  -0.0305   1.0000   0.0385
  -6.500  -0.3299   0.08720   0.08291  -0.0338   0.9982   0.0387
  -6.250  -0.2985   0.08212   0.07775  -0.0431   0.9911   0.0388
  -6.000  -0.2919   0.07665   0.07237  -0.0402   0.9875   0.0401
  -5.750  -0.2719   0.07285   0.06855  -0.0423   0.9817   0.0418
  -5.500  -0.2435   0.06898   0.06462  -0.0481   0.9758   0.0466
  -5.250  -0.1979   0.06315   0.05859  -0.0627   0.9670   0.0522
  -5.000  -0.1822   0.06001   0.05546  -0.0622   0.9615   0.0548
  -4.750  -0.1258   0.05592   0.05088  -0.0755   0.9541   0.0643
  -4.500  -0.1034   0.05074   0.04572  -0.0779   0.9472   0.0659
  -4.250  -0.0779   0.04795   0.04295  -0.0792   0.9408   0.0730
  -4.000  -0.0294   0.04061   0.03506  -0.0868   0.9345   0.0476
  -3.750   0.0072   0.03618   0.03025  -0.0905   0.9270   0.0449
  -3.500   0.0443   0.03269   0.02629  -0.0935   0.9204   0.0477
  -3.250   0.0777   0.02943   0.02256  -0.0952   0.9128   0.0471
  -3.000   0.1122   0.02673   0.01934  -0.0967   0.9061   0.0479
  -2.750   0.1449   0.02482   0.01687  -0.0974   0.8981   0.0503
  -2.500   0.1772   0.02301   0.01462  -0.0982   0.8917   0.0503
  -2.250   0.2072   0.02162   0.01287  -0.0984   0.8844   0.0506
  -2.000   0.2394   0.02036   0.01130  -0.0990   0.8785   0.0516
  -1.750   0.2674   0.01935   0.01023  -0.0991   0.8704   0.0549
  -1.500   0.2983   0.01849   0.00920  -0.0994   0.8637   0.0560
  -1.250   0.3271   0.01774   0.00834  -0.0992   0.8556   0.0564
  -1.000   0.3560   0.01710   0.00763  -0.0991   0.8476   0.0570
  -0.750   0.3853   0.01654   0.00700  -0.0991   0.8397   0.0581
  -0.500   0.4124   0.01614   0.00655  -0.0987   0.8304   0.0595
  -0.250   0.4423   0.01576   0.00608  -0.0987   0.8221   0.0617
   0.000   0.4699   0.01551   0.00573  -0.0983   0.8120   0.0644
   0.250   0.4975   0.01527   0.00548  -0.0980   0.8018   0.0705
   0.500   0.5271   0.01503   0.00526  -0.0980   0.7922   0.0905
   1.000   0.5941   0.01287   0.00504  -0.1000   0.7700   1.0000
   1.250   0.6210   0.01296   0.00497  -0.0995   0.7578   1.0000
   1.500   0.6477   0.01305   0.00495  -0.0989   0.7451   1.0000
   1.750   0.6741   0.01316   0.00494  -0.0984   0.7316   1.0000
   2.000   0.7002   0.01328   0.00496  -0.0977   0.7172   1.0000
   2.250   0.7260   0.01341   0.00503  -0.0970   0.7018   1.0000
   2.500   0.7511   0.01354   0.00510  -0.0962   0.6835   1.0000
   2.750   0.7761   0.01366   0.00512  -0.0953   0.6626   1.0000
   3.000   0.7999   0.01379   0.00518  -0.0942   0.6372   1.0000
   3.250   0.8238   0.01394   0.00523  -0.0932   0.6096   1.0000
   3.500   0.8480   0.01412   0.00529  -0.0921   0.5839   1.0000
   3.750   0.8725   0.01436   0.00540  -0.0913   0.5629   1.0000
   4.000   0.8970   0.01464   0.00562  -0.0905   0.5455   1.0000
   4.250   0.9215   0.01496   0.00587  -0.0897   0.5292   1.0000
   4.500   0.9458   0.01529   0.00618  -0.0890   0.5137   1.0000
   4.750   0.9701   0.01565   0.00654  -0.0882   0.4986   1.0000
   5.000   0.9942   0.01602   0.00692  -0.0875   0.4843   1.0000
   5.250   1.0180   0.01640   0.00732  -0.0867   0.4693   1.0000
   5.500   1.0414   0.01678   0.00775  -0.0858   0.4534   1.0000
   5.750   1.0645   0.01718   0.00823  -0.0849   0.4368   1.0000
   6.000   1.0872   0.01758   0.00871  -0.0840   0.4193   1.0000
   6.250   1.1088   0.01801   0.00917  -0.0828   0.3984   1.0000
   6.500   1.1290   0.01844   0.00965  -0.0815   0.3697   1.0000
   6.750   1.1483   0.01893   0.01017  -0.0801   0.3334   1.0000
   7.000   1.1663   0.01955   0.01070  -0.0785   0.2958   1.0000
   7.250   1.1841   0.02028   0.01135  -0.0769   0.2665   1.0000
   7.500   1.2005   0.02116   0.01211  -0.0753   0.2394   1.0000
   7.750   1.2153   0.02218   0.01299  -0.0735   0.2084   1.0000
   8.000   1.2300   0.02319   0.01390  -0.0718   0.1797   1.0000
   8.250   1.2460   0.02410   0.01486  -0.0703   0.1565   1.0000
   8.500   1.2621   0.02498   0.01580  -0.0687   0.1315   1.0000
   8.750   1.2722   0.02636   0.01689  -0.0666   0.0852   1.0000
   9.000   1.2788   0.02808   0.01838  -0.0640   0.0543   1.0000
   9.250   1.2846   0.02981   0.02006  -0.0611   0.0371   1.0000
   9.500   1.2897   0.03142   0.02166  -0.0582   0.0298   1.0000
   9.750   1.2954   0.03293   0.02330  -0.0555   0.0259   1.0000
  10.000   1.2975   0.03476   0.02520  -0.0527   0.0233   1.0000
  10.250   1.2989   0.03664   0.02729  -0.0500   0.0222   1.0000
  10.500   1.2999   0.03862   0.02949  -0.0475   0.0214   1.0000
  10.750   1.2998   0.04078   0.03186  -0.0453   0.0207   1.0000
  11.000   1.2993   0.04310   0.03438  -0.0434   0.0198   1.0000
  11.250   1.2981   0.04562   0.03708  -0.0418   0.0189   1.0000
  11.500   1.2966   0.04830   0.03994  -0.0404   0.0181   1.0000
  11.750   1.2941   0.05121   0.04301  -0.0394   0.0172   1.0000
  12.000   1.2913   0.05431   0.04627  -0.0386   0.0166   1.0000
  12.250   1.2882   0.05762   0.04974  -0.0379   0.0162   1.0000
  12.500   1.2854   0.06109   0.05338  -0.0374   0.0158   1.0000
  12.750   1.2821   0.06480   0.05727  -0.0370   0.0155   1.0000
  13.000   1.2793   0.06862   0.06128  -0.0368   0.0153   1.0000
  13.250   1.2744   0.07291   0.06580  -0.0369   0.0150   1.0000
  13.500   1.2679   0.07753   0.07065  -0.0374   0.0149   1.0000
  13.750   1.2586   0.08270   0.07608  -0.0385   0.0147   1.0000
  14.000   1.2483   0.08808   0.08169  -0.0402   0.0147   1.0000
  14.250   1.2363   0.09399   0.08780  -0.0425   0.0147   1.0000
  14.500   1.2234   0.10026   0.09429  -0.0454   0.0147   1.0000
  14.750   1.2098   0.10700   0.10125  -0.0489   0.0147   1.0000
  15.250   1.1821   0.12161   0.11629  -0.0574   0.0147   1.0000
  15.500   1.1681   0.12959   0.12444  -0.0624   0.0148   1.0000
  15.750   1.1549   0.13789   0.13290  -0.0677   0.0149   1.0000
  16.000   1.1408   0.14710   0.14226  -0.0737   0.0151   1.0000
  16.250   1.1247   0.15785   0.15315  -0.0807   0.0154   1.0000
  16.500   1.0983   0.17391   0.16934  -0.0903   0.0161   1.0000
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