Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 16K AIRFOIL (goe16k-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 16K AIRFOIL (goe16k-il)
Reynolds number: 500,000
Max Cl/Cd: 50.64 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe16k-il-500000-n5.txt
Download as CSV file: xf-goe16k-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 16K AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.5226   0.11007   0.10670  -0.1483   0.9468   0.0225
 -19.500  -0.5656   0.09937   0.09586  -0.1541   0.9464   0.0227
 -19.250  -0.5959   0.09100   0.08735  -0.1588   0.9460   0.0228
 -19.000  -0.6344   0.08551   0.08177  -0.1575   0.9403   0.0225
 -18.750  -0.6719   0.07725   0.07337  -0.1614   0.9385   0.0233
 -18.500  -0.6918   0.07139   0.06738  -0.1646   0.9371   0.0232
 -18.250  -0.7155   0.06490   0.06077  -0.1683   0.9360   0.0234
 -18.000  -0.7309   0.05942   0.05515  -0.1718   0.9350   0.0237
 -17.750  -0.7448   0.05395   0.04954  -0.1754   0.9342   0.0238
 -17.500  -0.7672   0.04988   0.04536  -0.1750   0.9289   0.0247
 -17.250  -0.7787   0.04578   0.04112  -0.1767   0.9259   0.0251
 -17.000  -0.7805   0.04252   0.03773  -0.1783   0.9240   0.0261
 -16.750  -0.7859   0.03912   0.03420  -0.1796   0.9225   0.0261
 -16.500  -0.7830   0.03675   0.03174  -0.1803   0.9213   0.0271
 -16.250  -0.7880   0.03496   0.02986  -0.1786   0.9174   0.0278
 -16.000  -0.7910   0.03339   0.02822  -0.1766   0.9132   0.0287
 -15.750  -0.7846   0.03200   0.02673  -0.1757   0.9110   0.0297
 -15.500  -0.7755   0.03069   0.02530  -0.1751   0.9094   0.0307
 -15.250  -0.7684   0.02918   0.02366  -0.1743   0.9082   0.0308
 -15.000  -0.7497   0.02838   0.02286  -0.1745   0.9072   0.0325
 -14.750  -0.7305   0.02756   0.02196  -0.1748   0.9064   0.0341
 -14.500  -0.7364   0.02684   0.02116  -0.1701   0.9000   0.0344
 -14.250  -0.7231   0.02607   0.02028  -0.1690   0.8976   0.0353
 -14.000  -0.7067   0.02530   0.01943  -0.1684   0.8959   0.0364
 -13.750  -0.6888   0.02454   0.01862  -0.1681   0.8945   0.0373
 -13.500  -0.6655   0.02400   0.01803  -0.1685   0.8934   0.0386
 -13.250  -0.6427   0.02332   0.01725  -0.1689   0.8923   0.0393
 -13.000  -0.6174   0.02277   0.01661  -0.1697   0.8913   0.0408
 -12.750  -0.6188   0.02253   0.01629  -0.1646   0.8852   0.0415
 -12.500  -0.6017   0.02203   0.01570  -0.1636   0.8825   0.0419
 -12.250  -0.5835   0.02140   0.01499  -0.1628   0.8805   0.0426
 -12.000  -0.5613   0.02090   0.01446  -0.1628   0.8788   0.0440
 -11.750  -0.5366   0.02044   0.01393  -0.1631   0.8774   0.0448
 -11.500  -0.5099   0.02005   0.01347  -0.1639   0.8761   0.0461
 -11.250  -0.5024   0.01979   0.01316  -0.1603   0.8726   0.0468
 -11.000  -0.4948   0.01950   0.01281  -0.1568   0.8691   0.0473
 -10.750  -0.4770   0.01925   0.01248  -0.1554   0.8667   0.0483
 -10.500  -0.4559   0.01894   0.01208  -0.1547   0.8648   0.0490
 -10.250  -0.4328   0.01859   0.01166  -0.1544   0.8632   0.0496
 -10.000  -0.4130   0.01793   0.01095  -0.1537   0.8617   0.0507
  -9.750  -0.3877   0.01750   0.01048  -0.1539   0.8604   0.0516
  -9.500  -0.3600   0.01713   0.01006  -0.1546   0.8593   0.0530
  -9.250  -0.3640   0.01709   0.01001  -0.1482   0.8557   0.0535
  -9.000  -0.3555   0.01690   0.00978  -0.1445   0.8531   0.0537
  -8.750  -0.3417   0.01666   0.00949  -0.1420   0.8509   0.0544
  -8.500  -0.3243   0.01639   0.00917  -0.1403   0.8490   0.0550
  -8.250  -0.3012   0.01619   0.00892  -0.1397   0.8475   0.0563
  -8.000  -0.2781   0.01587   0.00855  -0.1392   0.8461   0.0567
  -7.750  -0.2520   0.01560   0.00821  -0.1394   0.8449   0.0573
  -7.500  -0.2243   0.01535   0.00790  -0.1398   0.8439   0.0580
  -7.250  -0.1975   0.01495   0.00747  -0.1402   0.8430   0.0593
  -7.000  -0.1927   0.01487   0.00738  -0.1355   0.8408   0.0601
  -6.750  -0.1899   0.01483   0.00733  -0.1303   0.8383   0.0605
  -6.500  -0.1783   0.01473   0.00722  -0.1270   0.8364   0.0616
  -6.250  -0.1627   0.01461   0.00709  -0.1247   0.8347   0.0629
  -6.000  -0.1442   0.01448   0.00693  -0.1231   0.8332   0.0635
  -5.750  -0.1235   0.01434   0.00677  -0.1218   0.8319   0.0654
  -5.500  -0.1010   0.01422   0.00662  -0.1210   0.8307   0.0662
  -5.250  -0.0768   0.01408   0.00645  -0.1205   0.8297   0.0675
  -5.000  -0.0505   0.01389   0.00626  -0.1206   0.8288   0.0697
  -4.750  -0.0222   0.01372   0.00608  -0.1211   0.8280   0.0718
  -4.500   0.0071   0.01354   0.00590  -0.1218   0.8272   0.0763
  -4.250   0.0390   0.01333   0.00572  -0.1231   0.8264   0.0842
  -4.000   0.0515   0.01333   0.00574  -0.1200   0.8248   0.0897
  -3.750   0.0385   0.01355   0.00601  -0.1111   0.8217   0.0968
  -3.500   0.0461   0.01347   0.00610  -0.1071   0.8196   0.1305
  -3.250   0.0611   0.01335   0.00615  -0.1047   0.8180   0.1687
  -3.000   0.0799   0.01332   0.00616  -0.1030   0.8165   0.1832
  -2.750   0.1016   0.01325   0.00615  -0.1020   0.8153   0.2022
  -2.250   0.1524   0.01301   0.00607  -0.1016   0.8132   0.2441
  -2.000   0.1783   0.01290   0.00605  -0.1016   0.8123   0.2696
  -1.500   0.2328   0.01266   0.00602  -0.1021   0.8108   0.3283
  -1.250   0.2621   0.01255   0.00599  -0.1028   0.8101   0.3518
  -1.000   0.2188   0.01335   0.00679  -0.0872   0.8034   0.3459
  -0.750   0.2286   0.01341   0.00695  -0.0836   0.8002   0.3697
  -0.500   0.2558   0.01325   0.00683  -0.0837   0.7983   0.3891
  -0.250   0.2832   0.01306   0.00676  -0.0839   0.7970   0.4211
   0.000   0.3120   0.01288   0.00667  -0.0844   0.7959   0.4469
   0.250   0.3425   0.01257   0.00652  -0.0853   0.7948   0.4929
   0.500   0.3640   0.01196   0.00633  -0.0842   0.7934   0.6092
   0.750   0.2964   0.01282   0.00757  -0.0636   0.7841   0.6916
   1.750   0.5767   0.01458   0.01005  -0.1015   0.7834   0.9299
   2.000   0.6153   0.01482   0.01031  -0.1041   0.7821   0.9331
   2.250   0.6463   0.01511   0.01059  -0.1050   0.7809   0.9390
   2.500   0.6716   0.01511   0.01058  -0.1046   0.7791   0.9430
   2.750   0.7138   0.01503   0.01050  -0.1081   0.7778   0.9443
   3.000   0.7571   0.01495   0.01042  -0.1118   0.7767   0.9457
   3.250   0.7108   0.01644   0.01199  -0.0961   0.7669   0.9542
   3.500   0.7536   0.01617   0.01171  -0.0995   0.7631   0.9551
   3.750   0.7933   0.01614   0.01169  -0.1025   0.7618   0.9565
   4.000   0.7835   0.01708   0.01270  -0.0950   0.7536   0.9597
   4.250   0.8158   0.01679   0.01235  -0.0959   0.7449   0.9625
   4.500   0.8044   0.01800   0.01365  -0.0885   0.7381   0.9659
   4.750   0.8341   0.01820   0.01386  -0.0893   0.7267   0.9683
   5.000   0.8362   0.01891   0.01457  -0.0845   0.7067   0.9708
   5.250   0.8593   0.01904   0.01459  -0.0835   0.6819   0.9749
   5.500   0.8904   0.01893   0.01438  -0.0847   0.6575   0.9759
   5.750   0.9015   0.01947   0.01461  -0.0817   0.6106   0.9775
   6.000   0.9050   0.02040   0.01537  -0.0776   0.5746   0.9796
   6.250   0.8870   0.02212   0.01682  -0.0694   0.5151   0.9824
   6.500   0.8711   0.02409   0.01847  -0.0622   0.4565   0.9854
   6.750   0.8763   0.02513   0.01936  -0.0591   0.4266   0.9864
   7.000   0.8894   0.02586   0.02000  -0.0573   0.4054   0.9876
   7.250   0.9031   0.02654   0.02062  -0.0555   0.3888   0.9887
   7.500   0.9167   0.02721   0.02123  -0.0538   0.3721   0.9899
   7.750   0.9306   0.02789   0.02186  -0.0520   0.3532   0.9910
   8.000   0.9424   0.02876   0.02262  -0.0500   0.3263   0.9926
   8.500   0.9690   0.03057   0.02413  -0.0472   0.2627   0.9956
   8.750   0.9832   0.03138   0.02480  -0.0461   0.2332   0.9970
   9.000   0.9939   0.03230   0.02555  -0.0442   0.2022   0.9980
   9.250   1.0085   0.03293   0.02615  -0.0427   0.1903   0.9985
   9.500   1.0192   0.03376   0.02686  -0.0407   0.1703   0.9990
   9.750   1.0323   0.03439   0.02746  -0.0390   0.1583   0.9992
  10.000   1.0443   0.03509   0.02810  -0.0371   0.1446   0.9993
  10.250   1.0561   0.03580   0.02876  -0.0352   0.1338   0.9994
  10.500   1.0674   0.03656   0.02948  -0.0333   0.1238   0.9995
  10.750   1.0801   0.03723   0.03015  -0.0316   0.1151   0.9995
  11.000   1.0913   0.03801   0.03087  -0.0297   0.1043   0.9996
  11.250   1.1049   0.03865   0.03152  -0.0281   0.1010   0.9997
  11.500   1.1137   0.03961   0.03239  -0.0261   0.0870   0.9997
  11.750   1.1272   0.04028   0.03312  -0.0245   0.0870   0.9998
  12.000   1.1391   0.04105   0.03389  -0.0228   0.0823   0.9998
  12.250   1.1499   0.04188   0.03470  -0.0211   0.0755   0.9998
  12.500   1.1611   0.04272   0.03556  -0.0194   0.0732   0.9998
  12.750   1.1718   0.04359   0.03644  -0.0176   0.0674   0.9998
  13.000   1.1839   0.04439   0.03728  -0.0161   0.0664   0.9998
  13.250   1.1943   0.04532   0.03824  -0.0144   0.0625   0.9999
  13.500   1.2051   0.04624   0.03919  -0.0129   0.0592   0.9999
  13.750   1.2137   0.04733   0.04026  -0.0111   0.0548   0.9999
  14.000   1.2237   0.04832   0.04128  -0.0095   0.0505   0.9999
  14.250   1.2323   0.04943   0.04240  -0.0078   0.0466   0.9999
  14.750   1.2486   0.05177   0.04477  -0.0045   0.0388   0.9999
  15.000   1.2554   0.05307   0.04607  -0.0028   0.0345   0.9999
  15.250   1.2621   0.05441   0.04745  -0.0012   0.0320   0.9999
  15.500   1.2705   0.05563   0.04873   0.0002   0.0314   0.9999
  15.750   1.2745   0.05725   0.05035   0.0019   0.0280   0.9999
  16.000   1.2807   0.05871   0.05186   0.0034   0.0263   0.9999
  16.250   1.2857   0.06028   0.05348   0.0049   0.0249   0.9999
  16.500   1.2904   0.06193   0.05518   0.0063   0.0244   0.9999
  16.750   1.2955   0.06356   0.05688   0.0077   0.0232   0.9999
  17.000   1.2993   0.06533   0.05871   0.0090   0.0220   0.9999
  17.250   1.3036   0.06709   0.06053   0.0102   0.0210   0.9999
  17.500   1.3040   0.06927   0.06276   0.0116   0.0200   0.9999
  17.750   1.3070   0.07123   0.06480   0.0127   0.0192   0.9999
  18.000   1.3091   0.07331   0.06696   0.0137   0.0187   0.9999
  18.250   1.3123   0.07530   0.06900   0.0146   0.0179   0.9998
  18.500   1.3123   0.07766   0.07145   0.0155   0.0175   0.9998
  18.750   1.3101   0.08034   0.07421   0.0164   0.0167   0.9998
  19.000   1.3087   0.08294   0.07688   0.0171   0.0168   0.9998
  19.250   1.3075   0.08557   0.07961   0.0177   0.0167   0.9998
<< Back to GOE 16K AIRFOIL (goe16k-il)

Polar data table (+)

Polar graphs


<< Back to GOE 16K AIRFOIL (goe16k-il)