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GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 500 AIRFOIL (goe500-il)
Reynolds number: 200,000
Max Cl/Cd: 92.04 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe500-il-200000.txt
Download as CSV file: xf-goe500-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 500 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1686   0.09534   0.09209  -0.0573   0.9754   0.0606
  -8.750  -0.1556   0.09144   0.08817  -0.0604   0.9729   0.0633
  -8.500  -0.2733   0.10178   0.09841  -0.0492   0.9852   0.0588
  -8.250  -0.2515   0.09847   0.09508  -0.0524   0.9832   0.0608
  -8.000  -0.2409   0.09546   0.09208  -0.0550   0.9773   0.0635
  -7.750  -0.2417   0.09234   0.08898  -0.0665   0.9682   0.0673
  -7.500  -0.2346   0.08687   0.08354  -0.0728   0.9598   0.0681
  -7.250  -0.2094   0.08456   0.08119  -0.0682   0.9598   0.0701
  -7.000  -0.1845   0.08153   0.07813  -0.0716   0.9570   0.0735
  -6.750  -0.1619   0.07426   0.07079  -0.0974   0.9426   0.0795
  -6.500  -0.1469   0.07025   0.06681  -0.0942   0.9413   0.0808
  -6.250  -0.1392   0.06870   0.06527  -0.0909   0.9334   0.0819
  -6.000  -0.1145   0.06648   0.06303  -0.0922   0.9297   0.0854
  -5.750  -0.0702   0.04185   0.03775  -0.1311   0.9188   0.0663
  -5.500  -0.0304   0.03219   0.02734  -0.1426   0.9147   0.0636
  -5.250   0.0132   0.02664   0.02093  -0.1493   0.9128   0.0646
  -5.000   0.0560   0.02387   0.01753  -0.1534   0.9113   0.0665
  -4.750   0.0976   0.02196   0.01528  -0.1567   0.9101   0.0696
  -4.500   0.1156   0.02140   0.01464  -0.1550   0.9012   0.0716
  -4.250   0.1544   0.02042   0.01347  -0.1571   0.8986   0.0752
  -4.000   0.1947   0.01955   0.01232  -0.1593   0.8963   0.0797
  -3.750   0.2360   0.01853   0.01133  -0.1617   0.8944   0.0863
  -3.500   0.2596   0.01812   0.01075  -0.1606   0.8850   0.0923
  -3.250   0.2971   0.01722   0.00986  -0.1621   0.8815   0.1040
  -3.000   0.3346   0.01649   0.00908  -0.1637   0.8791   0.1210
  -2.750   0.3567   0.01614   0.00876  -0.1626   0.8706   0.1353
  -2.500   0.3896   0.01566   0.00827  -0.1634   0.8666   0.1511
  -2.250   0.4245   0.01519   0.00781  -0.1645   0.8638   0.1661
  -2.000   0.4474   0.01505   0.00771  -0.1635   0.8554   0.1785
  -1.750   0.4793   0.01468   0.00737  -0.1640   0.8510   0.1940
  -1.500   0.5135   0.01426   0.00698  -0.1648   0.8479   0.2120
  -1.250   0.5362   0.01415   0.00693  -0.1637   0.8388   0.2308
  -1.000   0.5683   0.01371   0.00665  -0.1642   0.8346   0.2689
  -0.750   0.5948   0.01348   0.00658  -0.1638   0.8275   0.3252
  -0.500   0.6239   0.01320   0.00642  -0.1638   0.8213   0.3744
  -0.250   0.6545   0.01292   0.00623  -0.1639   0.8161   0.4164
   0.000   0.6797   0.01281   0.00622  -0.1632   0.8076   0.4559
   0.250   0.7112   0.01252   0.00601  -0.1635   0.8028   0.5012
   0.500   0.7353   0.01243   0.00608  -0.1626   0.7936   0.5469
   0.750   0.7656   0.01211   0.00587  -0.1627   0.7879   0.6066
   1.000   0.7882   0.01188   0.00589  -0.1613   0.7782   0.6859
   1.250   0.8209   0.01122   0.00559  -0.1616   0.7717   1.0000
   1.500   0.8473   0.01129   0.00559  -0.1612   0.7618   1.0000
   1.750   0.8757   0.01134   0.00555  -0.1610   0.7533   1.0000
   2.000   0.9044   0.01137   0.00550  -0.1609   0.7444   1.0000
   2.250   0.9309   0.01149   0.00556  -0.1605   0.7340   1.0000
   2.500   0.9594   0.01156   0.00556  -0.1603   0.7246   1.0000
   2.750   0.9864   0.01167   0.00561  -0.1600   0.7139   1.0000
   3.000   1.0124   0.01184   0.00575  -0.1595   0.7028   1.0000
   3.250   1.0396   0.01199   0.00585  -0.1591   0.6922   1.0000
   3.500   1.0671   0.01214   0.00594  -0.1589   0.6815   1.0000
   3.750   1.0919   0.01234   0.00614  -0.1582   0.6691   1.0000
   4.000   1.1174   0.01253   0.00632  -0.1575   0.6568   1.0000
   4.250   1.1427   0.01272   0.00648  -0.1569   0.6439   1.0000
   4.500   1.1676   0.01290   0.00663  -0.1561   0.6302   1.0000
   4.750   1.1919   0.01308   0.00677  -0.1552   0.6156   1.0000
   5.000   1.2158   0.01328   0.00695  -0.1543   0.6010   1.0000
   5.250   1.2392   0.01349   0.00714  -0.1533   0.5862   1.0000
   5.500   1.2616   0.01371   0.00735  -0.1521   0.5702   1.0000
   5.750   1.2831   0.01394   0.00757  -0.1507   0.5527   1.0000
   6.000   1.3041   0.01420   0.00783  -0.1493   0.5347   1.0000
   6.250   1.3244   0.01448   0.00808  -0.1478   0.5159   1.0000
   6.500   1.3442   0.01483   0.00837  -0.1462   0.4972   1.0000
   6.750   1.3626   0.01519   0.00873  -0.1443   0.4763   1.0000
   7.000   1.3802   0.01560   0.00913  -0.1424   0.4554   1.0000
   7.250   1.3960   0.01608   0.00957  -0.1402   0.4319   1.0000
   7.500   1.4083   0.01665   0.01006  -0.1373   0.4022   1.0000
   7.750   1.4151   0.01736   0.01065  -0.1336   0.3584   1.0000
   8.000   1.4072   0.01860   0.01147  -0.1276   0.2802   1.0000
   8.250   1.3896   0.02083   0.01306  -0.1208   0.1922   1.0000
   8.500   1.3731   0.02348   0.01509  -0.1149   0.1104   1.0000
   8.750   1.3698   0.02547   0.01686  -0.1110   0.0822   1.0000
   9.000   1.3720   0.02713   0.01847  -0.1078   0.0721   1.0000
   9.250   1.3767   0.02867   0.02005  -0.1051   0.0657   1.0000
   9.500   1.3768   0.03060   0.02201  -0.1021   0.0614   1.0000
   9.750   1.3826   0.03219   0.02370  -0.0999   0.0579   1.0000
  10.000   1.3858   0.03404   0.02560  -0.0975   0.0548   1.0000
  10.250   1.3838   0.03647   0.02803  -0.0949   0.0521   1.0000
  10.500   1.3897   0.03833   0.03001  -0.0930   0.0497   1.0000
  10.750   1.3965   0.04016   0.03193  -0.0912   0.0475   1.0000
  11.000   1.4033   0.04207   0.03389  -0.0896   0.0454   1.0000
  11.250   1.4105   0.04414   0.03594  -0.0880   0.0433   1.0000
  11.500   1.4235   0.04611   0.03794  -0.0865   0.0411   1.0000
  11.750   1.4360   0.04774   0.03970  -0.0852   0.0394   1.0000
  12.000   1.4508   0.04941   0.04148  -0.0840   0.0378   1.0000
  12.250   1.4658   0.05114   0.04327  -0.0830   0.0363   1.0000
  12.500   1.5063   0.05327   0.04531  -0.0832   0.0337   1.0000
  12.750   1.5084   0.05530   0.04759  -0.0815   0.0329   1.0000
  13.000   1.5171   0.05757   0.05010  -0.0802   0.0320   1.0000
  13.250   1.5270   0.06012   0.05289  -0.0790   0.0312   1.0000
  13.500   1.5348   0.06293   0.05593  -0.0778   0.0305   1.0000
  13.750   1.5398   0.06593   0.05916  -0.0767   0.0299   1.0000
  14.000   1.5431   0.06892   0.06233  -0.0757   0.0293   1.0000
  14.250   1.5489   0.07169   0.06519  -0.0750   0.0285   1.0000
  14.500   1.5526   0.07500   0.06861  -0.0744   0.0277   1.0000
  15.000   1.5394   0.08572   0.07984  -0.0734   0.0269   1.0000
  15.250   1.5232   0.09048   0.08486  -0.0732   0.0269   1.0000
  15.500   1.5070   0.09570   0.09034  -0.0735   0.0269   1.0000
  15.750   1.4901   0.10130   0.09620  -0.0744   0.0269   1.0000
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