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GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 381 AIRFOIL (goe381-il)
Reynolds number: 100,000
Max Cl/Cd: 61.52 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe381-il-100000-n5.txt
Download as CSV file: xf-goe381-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 381 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2675   0.09832   0.09409  -0.0224   1.0000   0.0282
  -7.000  -0.2757   0.09731   0.09318  -0.0205   1.0000   0.0285
  -6.750  -0.2789   0.09595   0.09189  -0.0202   0.9992   0.0288
  -6.500  -0.2503   0.09245   0.08838  -0.0290   0.9909   0.0293
  -6.250  -0.2193   0.08879   0.08465  -0.0379   0.9830   0.0295
  -6.000  -0.1857   0.08486   0.08066  -0.0468   0.9763   0.0297
  -5.750  -0.1531   0.08089   0.07663  -0.0544   0.9688   0.0298
  -5.500  -0.1191   0.07675   0.07240  -0.0615   0.9624   0.0298
  -5.250  -0.0827   0.07274   0.06828  -0.0685   0.9557   0.0300
  -5.000  -0.0796   0.06652   0.06221  -0.0655   0.9509   0.0315
  -4.750  -0.0542   0.06292   0.05857  -0.0689   0.9428   0.0334
  -4.500  -0.0208   0.05927   0.05482  -0.0744   0.9356   0.0352
  -4.250   0.0162   0.05581   0.05122  -0.0802   0.9275   0.0379
  -4.000   0.0726   0.05370   0.04872  -0.0893   0.9185   0.0403
  -3.750   0.0957   0.04870   0.04374  -0.0916   0.9118   0.0416
  -3.500   0.1340   0.04757   0.04233  -0.0950   0.9016   0.0521
  -3.250   0.1579   0.04306   0.03780  -0.0968   0.8935   0.0541
  -3.000   0.1837   0.04021   0.03486  -0.0981   0.8843   0.0583
  -2.500   0.2479   0.03535   0.02957  -0.1017   0.8644   0.0720
  -2.250   0.2896   0.03193   0.02561  -0.1038   0.8554   0.0543
  -2.000   0.3200   0.02955   0.02294  -0.1043   0.8439   0.0499
  -1.750   0.3540   0.02784   0.02072  -0.1046   0.8327   0.0521
  -1.500   0.3832   0.02569   0.01827  -0.1049   0.8213   0.0514
  -1.250   0.4134   0.02400   0.01621  -0.1049   0.8093   0.0532
  -1.000   0.4393   0.02303   0.01517  -0.1049   0.7949   0.0579
  -0.750   0.4687   0.02160   0.01336  -0.1045   0.7794   0.0560
  -0.500   0.4975   0.02033   0.01167  -0.1039   0.7624   0.0545
  -0.250   0.5252   0.01929   0.01031  -0.1032   0.7438   0.0539
   0.000   0.5523   0.01840   0.00914  -0.1025   0.7240   0.0540
   0.250   0.5787   0.01769   0.00821  -0.1018   0.7018   0.0548
   0.500   0.6051   0.01713   0.00746  -0.1010   0.6820   0.0563
   0.750   0.6316   0.01669   0.00687  -0.1005   0.6646   0.0587
   1.000   0.6576   0.01637   0.00640  -0.0998   0.6494   0.0632
   1.250   0.6835   0.01627   0.00623  -0.0993   0.6345   0.0711
   1.500   0.7098   0.01609   0.00590  -0.0987   0.6204   0.0763
   1.750   0.7363   0.01596   0.00561  -0.0983   0.6066   0.0819
   2.000   0.7628   0.01592   0.00543  -0.0979   0.5925   0.0946
   2.250   0.7892   0.01593   0.00533  -0.0975   0.5784   0.1193
   2.500   0.8153   0.01598   0.00530  -0.0971   0.5639   0.1495
   3.000   0.8648   0.01485   0.00548  -0.0960   0.5340   1.0000
   3.250   0.8901   0.01511   0.00561  -0.0955   0.5184   1.0000
   3.500   0.9154   0.01539   0.00578  -0.0950   0.5026   1.0000
   3.750   0.9405   0.01566   0.00601  -0.0945   0.4864   1.0000
   4.000   0.9654   0.01594   0.00623  -0.0940   0.4692   1.0000
   4.250   0.9900   0.01623   0.00647  -0.0935   0.4504   1.0000
   4.500   1.0143   0.01655   0.00677  -0.0929   0.4303   1.0000
   4.750   1.0384   0.01688   0.00706  -0.0923   0.4080   1.0000
   5.000   1.0618   0.01727   0.00737  -0.0917   0.3850   1.0000
   5.250   1.0847   0.01772   0.00773  -0.0910   0.3621   1.0000
   5.500   1.1074   0.01821   0.00819  -0.0903   0.3422   1.0000
   5.750   1.1300   0.01873   0.00867  -0.0896   0.3253   1.0000
   6.000   1.1525   0.01927   0.00921  -0.0889   0.3105   1.0000
   6.250   1.1722   0.01999   0.00978  -0.0879   0.2823   1.0000
   6.500   1.1908   0.02082   0.01041  -0.0868   0.2499   1.0000
   6.750   1.2107   0.02155   0.01111  -0.0859   0.2275   1.0000
   7.000   1.2302   0.02232   0.01182  -0.0849   0.1999   1.0000
   7.250   1.2505   0.02303   0.01254  -0.0840   0.1687   1.0000
   7.500   1.2601   0.02486   0.01376  -0.0821   0.1094   1.0000
   7.750   1.2687   0.02688   0.01542  -0.0799   0.0297   1.0000
   8.000   1.2813   0.02841   0.01700  -0.0779   0.0232   1.0000
   8.250   1.2956   0.02967   0.01853  -0.0761   0.0205   1.0000
   8.500   1.3085   0.03102   0.02013  -0.0742   0.0190   1.0000
   8.750   1.3194   0.03249   0.02186  -0.0722   0.0181   1.0000
   9.000   1.3264   0.03408   0.02371  -0.0697   0.0174   1.0000
   9.250   1.3297   0.03590   0.02579  -0.0670   0.0167   1.0000
   9.500   1.3290   0.03807   0.02820  -0.0644   0.0160   1.0000
   9.750   1.3239   0.04066   0.03105  -0.0619   0.0152   1.0000
  10.000   1.3153   0.04372   0.03436  -0.0598   0.0147   1.0000
  10.250   1.3051   0.04717   0.03802  -0.0583   0.0143   1.0000
  10.500   1.2946   0.05093   0.04198  -0.0573   0.0140   1.0000
  10.750   1.2886   0.05444   0.04562  -0.0568   0.0139   1.0000
  11.000   1.2836   0.05800   0.04933  -0.0565   0.0138   1.0000
  11.250   1.2797   0.06151   0.05297  -0.0562   0.0137   1.0000
  11.500   1.2778   0.06478   0.05635  -0.0558   0.0136   1.0000
  11.750   1.2791   0.06760   0.05933  -0.0549   0.0135   1.0000
  12.000   1.2844   0.06989   0.06168  -0.0534   0.0134   1.0000
  12.250   1.2941   0.07176   0.06359  -0.0515   0.0133   1.0000
  12.500   1.3058   0.07366   0.06558  -0.0496   0.0131   1.0000
  12.750   1.3128   0.07625   0.06833  -0.0485   0.0129   1.0000
  13.000   1.3152   0.07943   0.07170  -0.0482   0.0125   1.0000
  13.250   1.3157   0.08289   0.07536  -0.0481   0.0121   1.0000
  13.500   1.3144   0.08665   0.07932  -0.0483   0.0118   1.0000
  13.750   1.3109   0.09076   0.08364  -0.0489   0.0116   1.0000
  14.000   1.3060   0.09516   0.08826  -0.0497   0.0115   1.0000
  14.250   1.2998   0.09991   0.09323  -0.0510   0.0114   1.0000
  14.500   1.2922   0.10500   0.09853  -0.0527   0.0115   1.0000
  14.750   1.2834   0.11044   0.10419  -0.0549   0.0115   1.0000
  15.000   1.2736   0.11622   0.11018  -0.0575   0.0116   1.0000
  15.250   1.2631   0.12234   0.11651  -0.0607   0.0117   1.0000
  15.500   1.2521   0.12883   0.12320  -0.0643   0.0118   1.0000
  15.750   1.2408   0.13572   0.13028  -0.0685   0.0118   1.0000
  16.000   1.2296   0.14294   0.13768  -0.0732   0.0119   1.0000
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