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GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 396 AIRFOIL (goe396-il)
Reynolds number: 100,000
Max Cl/Cd: 66.98 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe396-il-100000.txt
Download as CSV file: xf-goe396-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 396 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3091   0.09439   0.08997  -0.0251   1.0000   0.0477
  -6.750  -0.3146   0.09299   0.08867  -0.0239   1.0000   0.0491
  -6.500  -0.3213   0.09203   0.08781  -0.0230   1.0000   0.0504
  -6.250  -0.3289   0.09198   0.08785  -0.0235   1.0000   0.0515
  -6.000  -0.3310   0.09179   0.08771  -0.0255   1.0000   0.0520
  -5.750  -0.3258   0.09108   0.08701  -0.0289   1.0000   0.0523
  -5.500  -0.3264   0.08717   0.08317  -0.0278   1.0000   0.0529
  -5.250  -0.3334   0.08273   0.07881  -0.0214   1.0000   0.0543
  -5.000  -0.3320   0.08017   0.07623  -0.0199   1.0000   0.0558
  -4.750  -0.3274   0.07774   0.07382  -0.0199   1.0000   0.0579
  -4.500  -0.3186   0.07530   0.07138  -0.0212   1.0000   0.0605
  -4.250  -0.2677   0.07443   0.07025  -0.0362   0.9990   0.0654
  -4.000  -0.2547   0.06798   0.06390  -0.0358   0.9945   0.0672
  -3.750  -0.2265   0.06397   0.05985  -0.0391   0.9883   0.0719
  -3.500  -0.1630   0.05971   0.05532  -0.0527   0.9825   0.0798
  -3.250  -0.1399   0.05602   0.05164  -0.0540   0.9755   0.0845
  -3.000  -0.0852   0.05206   0.04743  -0.0635   0.9700   0.0942
  -2.750  -0.0433   0.04903   0.04416  -0.0692   0.9624   0.1070
  -2.500  -0.0022   0.04566   0.04066  -0.0741   0.9569   0.1213
  -2.250   0.0359   0.04284   0.03763  -0.0780   0.9493   0.1345
  -2.000   0.0782   0.03967   0.03429  -0.0822   0.9438   0.1492
  -1.750   0.1136   0.03719   0.03163  -0.0848   0.9361   0.1638
  -1.500   0.1557   0.03493   0.02916  -0.0885   0.9303   0.2026
  -1.250   0.1886   0.03285   0.02687  -0.0901   0.9223   0.2300
  -1.000   0.2590   0.02545   0.01765  -0.0949   0.9201   0.0876
  -0.750   0.3047   0.02385   0.01561  -0.0979   0.9157   0.1010
  -0.500   0.3369   0.02256   0.01393  -0.0983   0.9068   0.1085
  -0.250   0.3837   0.02165   0.01282  -0.1016   0.9022   0.1319
   0.000   0.4157   0.02085   0.01202  -0.1022   0.8929   0.1578
   0.250   0.4640   0.01988   0.01121  -0.1058   0.8888   0.2353
   0.500   0.4961   0.01963   0.01105  -0.1067   0.8790   0.2958
   0.750   0.5430   0.01877   0.01041  -0.1100   0.8746   0.3701
   1.000   0.5951   0.01725   0.00990  -0.1149   0.8668   1.0000
   1.250   0.6364   0.01706   0.00948  -0.1168   0.8604   1.0000
   1.500   0.6654   0.01710   0.00940  -0.1166   0.8490   1.0000
   1.750   0.6944   0.01709   0.00932  -0.1162   0.8373   1.0000
   2.000   0.7238   0.01702   0.00918  -0.1158   0.8253   1.0000
   2.250   0.7526   0.01694   0.00910  -0.1152   0.8132   1.0000
   2.500   0.7806   0.01688   0.00901  -0.1145   0.8012   1.0000
   2.750   0.8089   0.01685   0.00897  -0.1138   0.7902   1.0000
   3.000   0.8365   0.01684   0.00897  -0.1131   0.7791   1.0000
   3.250   0.8614   0.01689   0.00905  -0.1120   0.7659   1.0000
   3.500   0.8865   0.01692   0.00919  -0.1109   0.7526   1.0000
   3.750   0.9113   0.01698   0.00932  -0.1098   0.7394   1.0000
   4.000   0.9366   0.01696   0.00937  -0.1086   0.7255   1.0000
   4.250   0.9619   0.01695   0.00945  -0.1074   0.7115   1.0000
   4.500   0.9853   0.01685   0.00945  -0.1058   0.6933   1.0000
   4.750   1.0079   0.01611   0.00873  -0.1028   0.6591   1.0000
   5.000   1.0310   0.01609   0.00883  -0.1012   0.6371   1.0000
   5.250   1.0488   0.01578   0.00838  -0.0977   0.5846   1.0000
   5.500   1.0670   0.01593   0.00850  -0.0950   0.5356   1.0000
   5.750   1.0787   0.01648   0.00863  -0.0912   0.4381   1.0000
   6.000   1.0795   0.01841   0.00938  -0.0865   0.2383   1.0000
   6.250   1.0790   0.02135   0.01110  -0.0825   0.0754   1.0000
   6.500   1.0900   0.02306   0.01253  -0.0797   0.0504   1.0000
   6.750   1.1037   0.02438   0.01404  -0.0772   0.0454   1.0000
   7.000   1.1140   0.02592   0.01572  -0.0742   0.0428   1.0000
   7.250   1.1214   0.02780   0.01770  -0.0709   0.0412   1.0000
   7.500   1.1344   0.02973   0.01967  -0.0684   0.0405   1.0000
   7.750   1.1567   0.03188   0.02190  -0.0670   0.0399   1.0000
   8.000   1.1825   0.03403   0.02423  -0.0661   0.0381   1.0000
   8.250   1.2108   0.03676   0.02719  -0.0656   0.0367   1.0000
   8.500   1.2396   0.04049   0.03128  -0.0650   0.0380   1.0000
   8.750   1.2628   0.04510   0.03633  -0.0640   0.0398   1.0000
   9.000   1.2845   0.04831   0.03994  -0.0622   0.0424   1.0000
   9.250   1.2898   0.05343   0.04602  -0.0582   0.0484   1.0000
   9.500   1.2979   0.05890   0.05211  -0.0551   0.0560   1.0000
   9.750   1.2912   0.06591   0.05986  -0.0510   0.0684   1.0000
  10.000   1.2092   0.06290   0.05748  -0.0413   0.0675   1.0000
  10.250   1.1808   0.06706   0.06194  -0.0369   0.0691   1.0000
  10.500   1.1637   0.07301   0.06805  -0.0347   0.0736   1.0000
  10.750   1.1361   0.07712   0.07234  -0.0325   0.0735   1.0000
  11.000   1.1109   0.08206   0.07743  -0.0317   0.0739   1.0000
  11.250   1.0861   0.08756   0.08306  -0.0318   0.0742   1.0000
  11.500   1.0611   0.09351   0.08912  -0.0327   0.0746   1.0000
  11.750   1.0367   0.09977   0.09541  -0.0345   0.0749   1.0000
  12.000   1.0125   0.10627   0.10200  -0.0371   0.0751   1.0000
  12.250   0.9858   0.11325   0.10906  -0.0406   0.0753   1.0000
  12.500   0.9606   0.12018   0.11605  -0.0446   0.0754   1.0000
  12.750   0.9311   0.12730   0.12322  -0.0495   0.0754   1.0000
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