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GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 395 AIRFOIL (goe395-il)
Reynolds number: 100,000
Max Cl/Cd: 70.35 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe395-il-100000.txt
Download as CSV file: xf-goe395-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 395 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2763   0.11640   0.11189  -0.0306   1.0000   0.0560
  -8.750  -0.2982   0.11737   0.11295  -0.0253   1.0000   0.0563
  -8.500  -0.3111   0.11711   0.11275  -0.0219   1.0000   0.0570
  -8.250  -0.3201   0.11635   0.11204  -0.0195   0.9999   0.0579
  -8.000  -0.3072   0.11336   0.10904  -0.0229   0.9961   0.0599
  -7.750  -0.2970   0.11123   0.10691  -0.0265   0.9918   0.0620
  -7.500  -0.2936   0.11138   0.10708  -0.0314   0.9853   0.0632
  -7.250  -0.2805   0.11188   0.10758  -0.0417   0.9777   0.0637
  -7.000  -0.2695   0.10664   0.10236  -0.0426   0.9748   0.0643
  -6.750  -0.2593   0.10042   0.09612  -0.0381   0.9742   0.0657
  -6.500  -0.2456   0.09703   0.09272  -0.0390   0.9718   0.0681
  -6.250  -0.2317   0.09438   0.09005  -0.0418   0.9690   0.0711
  -6.000  -0.2285   0.09286   0.08855  -0.0428   0.9646   0.0734
  -5.750  -0.2000   0.09343   0.08905  -0.0568   0.9591   0.0762
  -5.500  -0.1785   0.08981   0.08541  -0.0630   0.9569   0.0770
  -5.250  -0.1756   0.08488   0.08052  -0.0582   0.9557   0.0781
  -5.000  -0.1739   0.08234   0.07798  -0.0556   0.9529   0.0794
  -4.750  -0.1681   0.08020   0.07585  -0.0549   0.9504   0.0816
  -4.500  -0.1529   0.07794   0.07356  -0.0572   0.9477   0.0855
  -4.250  -0.0892   0.07568   0.07108  -0.0769   0.9442   0.0911
  -4.000  -0.0825   0.07152   0.06698  -0.0737   0.9422   0.0924
  -3.750  -0.0670   0.06868   0.06412  -0.0736   0.9385   0.0949
  -3.500  -0.0453   0.06625   0.06164  -0.0761   0.9333   0.0989
  -3.250   0.0149   0.06257   0.05776  -0.0894   0.9290   0.1068
  -3.000   0.0470   0.05943   0.05458  -0.0922   0.9260   0.1112
  -2.750   0.1010   0.05717   0.05204  -0.1038   0.9207   0.1204
  -2.500   0.1156   0.05445   0.04938  -0.1025   0.9166   0.1228
  -2.250   0.1728   0.05161   0.04632  -0.1119   0.9129   0.1360
  -2.000   0.2029   0.04944   0.04413  -0.1138   0.9092   0.1429
  -1.750   0.2374   0.04745   0.04199  -0.1180   0.9034   0.1523
  -1.500   0.2853   0.04521   0.03958  -0.1240   0.8991   0.1664
  -1.250   0.3366   0.04293   0.03718  -0.1298   0.8959   0.1834
  -1.000   0.3554   0.04202   0.03624  -0.1296   0.8885   0.2000
  -0.750   0.4004   0.04027   0.03437  -0.1340   0.8837   0.2278
  -0.500   0.5033   0.03455   0.02737  -0.1489   0.8820   0.1366
  -0.250   0.5395   0.03313   0.02554  -0.1507   0.8756   0.1325
   0.000   0.5838   0.03152   0.02357  -0.1537   0.8700   0.1366
   0.250   0.6391   0.03003   0.02169  -0.1582   0.8666   0.1503
   0.500   0.6606   0.02992   0.02148  -0.1573   0.8573   0.1643
   0.750   0.7064   0.02900   0.02058  -0.1601   0.8526   0.1852
   1.000   0.7322   0.02889   0.02042  -0.1597   0.8436   0.1988
   1.250   0.7725   0.02822   0.01964  -0.1610   0.8379   0.2087
   1.500   0.7984   0.02817   0.01962  -0.1605   0.8285   0.2207
   1.750   0.8365   0.02750   0.01900  -0.1612   0.8225   0.2321
   2.000   0.8618   0.02744   0.01899  -0.1603   0.8126   0.2433
   2.250   0.8982   0.02674   0.01836  -0.1605   0.8067   0.2663
   2.500   0.9220   0.02665   0.01850  -0.1593   0.7957   0.3032
   2.750   0.9556   0.02491   0.01784  -0.1586   0.7907   1.0000
   3.000   0.9784   0.02516   0.01798  -0.1571   0.7784   1.0000
   3.250   1.0040   0.02523   0.01799  -0.1559   0.7677   1.0000
   3.500   1.0366   0.02475   0.01747  -0.1552   0.7609   1.0000
   3.750   1.0601   0.02487   0.01763  -0.1537   0.7482   1.0000
   4.000   1.0854   0.02486   0.01763  -0.1524   0.7366   1.0000
   4.250   1.1183   0.02411   0.01688  -0.1514   0.7295   1.0000
   4.500   1.1431   0.02388   0.01668  -0.1498   0.7157   1.0000
   4.750   1.1687   0.02349   0.01636  -0.1481   0.7019   1.0000
   5.000   1.1945   0.02306   0.01599  -0.1465   0.6878   1.0000
   5.250   1.2204   0.02263   0.01561  -0.1451   0.6735   1.0000
   5.500   1.2465   0.02208   0.01516  -0.1435   0.6583   1.0000
   5.750   1.2728   0.02141   0.01456  -0.1420   0.6419   1.0000
   6.000   1.2992   0.02081   0.01402  -0.1405   0.6250   1.0000
   6.250   1.3217   0.02064   0.01398  -0.1390   0.6035   1.0000
   6.500   1.3483   0.02003   0.01340  -0.1375   0.5820   1.0000
   6.750   1.3726   0.01974   0.01304  -0.1358   0.5545   1.0000
   7.000   1.3958   0.01984   0.01303  -0.1342   0.5261   1.0000
   7.250   1.4172   0.02029   0.01339  -0.1326   0.4974   1.0000
   7.500   1.4368   0.02093   0.01400  -0.1308   0.4675   1.0000
   7.750   1.4532   0.02165   0.01464  -0.1286   0.4322   1.0000
   8.000   1.4645   0.02250   0.01540  -0.1258   0.3872   1.0000
   8.250   1.4707   0.02364   0.01634  -0.1225   0.3313   1.0000
   8.500   1.4727   0.02520   0.01754  -0.1189   0.2684   1.0000
   8.750   1.4721   0.02709   0.01901  -0.1152   0.2137   1.0000
   9.000   1.4705   0.02902   0.02064  -0.1114   0.1789   1.0000
   9.250   1.4682   0.03115   0.02258  -0.1078   0.1544   1.0000
   9.500   1.4656   0.03346   0.02476  -0.1044   0.1308   1.0000
   9.750   1.4611   0.03610   0.02728  -0.1011   0.1064   1.0000
  10.000   1.4559   0.03893   0.02989  -0.0980   0.0871   1.0000
  10.250   1.4570   0.04140   0.03232  -0.0953   0.0741   1.0000
  10.500   1.4636   0.04355   0.03451  -0.0929   0.0660   1.0000
  10.750   1.4742   0.04580   0.03675  -0.0906   0.0601   1.0000
  11.000   1.4845   0.04779   0.03880  -0.0888   0.0551   1.0000
  11.250   1.5094   0.05034   0.04131  -0.0873   0.0510   1.0000
  11.500   1.5296   0.05283   0.04411  -0.0857   0.0488   1.0000
  11.750   1.5463   0.05569   0.04726  -0.0842   0.0468   1.0000
  12.000   1.5551   0.05846   0.05026  -0.0825   0.0450   1.0000
  12.250   1.5615   0.06126   0.05319  -0.0808   0.0432   1.0000
  12.500   1.5762   0.06630   0.05839  -0.0800   0.0415   1.0000
  12.750   1.5709   0.07050   0.06291  -0.0778   0.0413   1.0000
  13.000   1.5602   0.07444   0.06719  -0.0755   0.0412   1.0000
  13.250   1.5471   0.07872   0.07179  -0.0736   0.0412   1.0000
  13.500   1.5323   0.08335   0.07675  -0.0721   0.0413   1.0000
  13.750   1.5162   0.08839   0.08206  -0.0711   0.0414   1.0000
  14.000   1.4979   0.09292   0.08690  -0.0705   0.0415   1.0000
  14.250   1.4774   0.09775   0.09200  -0.0706   0.0417   1.0000
  14.500   1.4544   0.10305   0.09758  -0.0715   0.0420   1.0000
  14.750   1.4271   0.10940   0.10421  -0.0737   0.0424   1.0000
  15.000   1.3888   0.11843   0.11361  -0.0786   0.0433   1.0000
  15.250   1.3241   0.13566   0.13129  -0.0914   0.0454   1.0000
  15.500   1.2738   0.15499   0.15079  -0.1054   0.0488   1.0000
  15.750   1.2543   0.16715   0.16295  -0.1129   0.0505   1.0000
  16.000   1.2469   0.17564   0.17140  -0.1173   0.0513   1.0000
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