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GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 614 AIRFOIL (goe614-il)
Reynolds number: 100,000
Max Cl/Cd: 33.6 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe614-il-100000.txt
Download as CSV file: xf-goe614-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 614 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0212   0.10251   0.09788  -0.0917   0.9156   0.1573
  -8.500  -0.2074   0.07198   0.06731  -0.1107   0.8953   0.0899
  -8.250  -0.1989   0.06555   0.06080  -0.1171   0.8902   0.0884
  -8.000  -0.2476   0.05766   0.05261  -0.1190   0.8739   0.0858
  -7.750  -0.2921   0.05062   0.04494  -0.1178   0.8583   0.0836
  -7.500  -0.3016   0.04651   0.04027  -0.1162   0.8464   0.0829
  -7.250  -0.2759   0.04355   0.03696  -0.1178   0.8404   0.0840
  -7.000  -0.2394   0.04035   0.03332  -0.1207   0.8374   0.0853
  -6.750  -0.2371   0.03919   0.03192  -0.1173   0.8239   0.0859
  -6.500  -0.1969   0.03650   0.02881  -0.1197   0.8208   0.0871
  -6.250  -0.1869   0.03554   0.02761  -0.1170   0.8088   0.0881
  -6.000  -0.1459   0.03354   0.02523  -0.1190   0.8048   0.0899
  -5.750  -0.0973   0.03167   0.02342  -0.1223   0.8023   0.0934
  -5.500  -0.0868   0.03126   0.02295  -0.1193   0.7903   0.0958
  -5.250  -0.0413   0.02972   0.02125  -0.1219   0.7863   0.1020
  -5.000   0.0086   0.02819   0.01965  -0.1253   0.7835   0.1128
  -4.750   0.0156   0.02785   0.01947  -0.1218   0.7713   0.1211
  -4.500   0.0554   0.02637   0.01819  -0.1236   0.7669   0.1555
  -4.250   0.1065   0.02584   0.01760  -0.1270   0.7637   0.2036
  -4.000   0.1110   0.02632   0.01805  -0.1229   0.7505   0.2174
  -3.750   0.1593   0.02592   0.01757  -0.1260   0.7466   0.2423
  -3.500   0.1683   0.02629   0.01790  -0.1227   0.7350   0.2543
  -3.250   0.2097   0.02584   0.01738  -0.1246   0.7299   0.2727
  -3.000   0.2383   0.02568   0.01721  -0.1245   0.7227   0.2878
  -2.750   0.2596   0.02565   0.01716  -0.1232   0.7137   0.3028
  -2.500   0.3057   0.02510   0.01653  -0.1259   0.7093   0.3255
  -2.250   0.3109   0.02555   0.01698  -0.1220   0.6985   0.3387
  -2.000   0.3488   0.02523   0.01664  -0.1233   0.6931   0.3607
  -1.750   0.3746   0.02524   0.01659  -0.1228   0.6864   0.3783
  -1.500   0.3912   0.02543   0.01676  -0.1208   0.6779   0.3930
  -1.250   0.4339   0.02492   0.01617  -0.1229   0.6733   0.4115
  -1.000   0.4416   0.02535   0.01666  -0.1195   0.6644   0.4223
  -0.750   0.4715   0.02519   0.01645  -0.1197   0.6582   0.4394
  -0.500   0.5138   0.02480   0.01599  -0.1219   0.6541   0.4613
  -0.250   0.5122   0.02560   0.01685  -0.1171   0.6452   0.4756
   0.000   0.5424   0.02545   0.01675  -0.1172   0.6397   0.4987
   0.250   0.5856   0.02500   0.01627  -0.1195   0.6357   0.5306
   0.500   0.5795   0.02589   0.01734  -0.1140   0.6270   0.5483
   0.750   0.6068   0.02580   0.01734  -0.1137   0.6218   0.5829
   1.000   0.6484   0.02534   0.01692  -0.1156   0.6181   0.6317
   1.250   0.6458   0.02619   0.01803  -0.1108   0.6106   0.6670
   1.500   0.6665   0.02618   0.01830  -0.1093   0.6048   0.7404
   1.750   0.7888   0.02522   0.01745  -0.1267   0.6003   1.0000
   2.000   0.7916   0.02622   0.01837  -0.1230   0.5941   1.0000
   2.250   0.7990   0.02704   0.01911  -0.1199   0.5877   1.0000
   2.500   0.8373   0.02702   0.01888  -0.1215   0.5833   1.0000
   2.750   0.8713   0.02724   0.01892  -0.1226   0.5790   1.0000
   3.000   0.8476   0.02893   0.02071  -0.1147   0.5710   1.0000
   3.250   0.8857   0.02877   0.02039  -0.1161   0.5660   1.0000
   3.500   0.9459   0.02816   0.01949  -0.1211   0.5621   1.0000
   3.750   0.9015   0.03042   0.02196  -0.1100   0.5534   1.0000
   4.000   0.9379   0.03028   0.02168  -0.1112   0.5483   1.0000
   4.250   0.9970   0.02967   0.02084  -0.1160   0.5445   1.0000
   4.500   0.9438   0.03234   0.02373  -0.1039   0.5364   1.0000
   4.750   0.9658   0.03272   0.02405  -0.1030   0.5313   1.0000
   5.000   1.0288   0.03191   0.02305  -0.1082   0.5276   1.0000
   5.250   0.9731   0.03486   0.02617  -0.0962   0.5201   1.0000
   5.500   0.9669   0.03635   0.02768  -0.0917   0.5136   1.0000
   5.750   1.0473   0.03446   0.02559  -0.0986   0.5104   1.0000
   6.000   1.0750   0.03466   0.02572  -0.0985   0.5051   1.0000
   6.250   0.9591   0.04124   0.03259  -0.0813   0.4940   1.0000
   6.500   1.0745   0.03672   0.02782  -0.0907   0.4925   1.0000
   6.750   1.1508   0.03512   0.02603  -0.0971   0.4882   1.0000
   7.000   0.9109   0.05060   0.04203  -0.0708   0.4691   1.0000
   7.250   0.9863   0.04639   0.03771  -0.0732   0.4686   1.0000
   7.500   1.1016   0.04066   0.03177  -0.0804   0.4685   1.0000
   7.750   1.0164   0.04767   0.03896  -0.0706   0.4563   1.0000
   8.000   1.1098   0.04309   0.03423  -0.0754   0.4561   1.0000
   8.250   1.2039   0.03986   0.03083  -0.0822   0.4545   1.0000
   8.500   1.0261   0.05313   0.04445  -0.0654   0.4371   1.0000
   8.750   1.1001   0.04917   0.04041  -0.0677   0.4371   1.0000
   9.000   1.1821   0.04556   0.03670  -0.0716   0.4366   1.0000
   9.250   0.7821   0.09037   0.08205  -0.0603   0.3861   1.0000
   9.500   0.7203   0.10191   0.09369  -0.0614   0.3774   1.0000
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