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NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il)
Reynolds number: 50,000
Max Cl/Cd: 22.06 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20410-il-50000-n5.txt
Download as CSV file: xf-sc20410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0410 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4978   0.13178   0.12402  -0.0119   1.0000   0.0682
 -12.250  -0.5000   0.12787   0.12012  -0.0132   1.0000   0.0677
 -11.750  -0.6629   0.12137   0.11327  -0.0101   1.0000   0.0606
 -11.500  -0.6622   0.11639   0.10831  -0.0120   1.0000   0.0603
 -11.250  -0.6642   0.11083   0.10278  -0.0144   1.0000   0.0601
 -11.000  -0.6699   0.10427   0.09625  -0.0180   1.0000   0.0599
 -10.750  -0.6797   0.09662   0.08861  -0.0228   1.0000   0.0597
 -10.500  -0.6947   0.08910   0.08109  -0.0277   1.0000   0.0593
 -10.250  -0.7138   0.08223   0.07417  -0.0321   1.0000   0.0590
 -10.000  -0.7348   0.07630   0.06818  -0.0352   1.0000   0.0587
  -9.750  -0.7559   0.07131   0.06307  -0.0368   1.0000   0.0585
  -9.500  -0.7708   0.06642   0.05796  -0.0384   1.0000   0.0587
  -9.250  -0.7805   0.06175   0.05295  -0.0392   1.0000   0.0592
  -9.000  -0.7848   0.05724   0.04798  -0.0396   1.0000   0.0600
  -8.750  -0.7805   0.05326   0.04362  -0.0397   1.0000   0.0611
  -8.500  -0.7680   0.05032   0.04053  -0.0395   1.0000   0.0625
  -8.250  -0.7540   0.04738   0.03735  -0.0393   1.0000   0.0639
  -8.000  -0.7383   0.04459   0.03427  -0.0391   1.0000   0.0658
  -7.750  -0.7209   0.04195   0.03120  -0.0388   1.0000   0.0691
  -7.500  -0.7016   0.03925   0.02788  -0.0386   1.0000   0.0725
  -7.250  -0.6810   0.03707   0.02569  -0.0380   1.0000   0.0754
  -7.000  -0.6595   0.03537   0.02386  -0.0375   1.0000   0.0800
  -6.750  -0.6366   0.03360   0.02168  -0.0368   1.0000   0.0852
  -6.500  -0.6146   0.03198   0.02008  -0.0359   1.0000   0.0898
  -6.250  -0.5920   0.03070   0.01871  -0.0349   1.0000   0.0965
  -6.000  -0.5693   0.02944   0.01734  -0.0334   1.0000   0.1024
  -5.750  -0.5476   0.02841   0.01632  -0.0321   1.0000   0.1104
  -5.500  -0.5259   0.02741   0.01528  -0.0306   1.0000   0.1186
  -5.250  -0.5047   0.02647   0.01432  -0.0293   1.0000   0.1289
  -5.000  -0.4841   0.02548   0.01342  -0.0283   1.0000   0.1420
  -4.750  -0.4631   0.02445   0.01247  -0.0275   1.0000   0.1592
  -4.500  -0.4419   0.02323   0.01153  -0.0271   1.0000   0.1879
  -4.250  -0.4204   0.02165   0.01052  -0.0274   1.0000   0.2539
  -4.000  -0.4043   0.02002   0.01030  -0.0259   1.0000   0.4368
  -3.500  -0.3747   0.02134   0.01204  -0.0168   1.0000   0.6544
  -3.250  -0.3568   0.02194   0.01252  -0.0136   1.0000   0.6926
  -3.000  -0.3420   0.02255   0.01306  -0.0094   1.0000   0.7247
  -2.750  -0.3306   0.02316   0.01361  -0.0041   1.0000   0.7564
  -2.500  -0.3213   0.02356   0.01398   0.0016   1.0000   0.7838
  -2.250  -0.3096   0.02366   0.01403   0.0062   1.0000   0.8067
  -2.000  -0.2947   0.02353   0.01382   0.0095   1.0000   0.8246
  -1.750  -0.2781   0.02329   0.01350   0.0120   1.0000   0.8397
  -1.500  -0.2597   0.02300   0.01312   0.0138   1.0000   0.8523
  -1.250  -0.2397   0.02272   0.01276   0.0149   1.0000   0.8633
  -1.000  -0.2191   0.02241   0.01238   0.0159   1.0000   0.8722
  -0.750  -0.1967   0.02214   0.01205   0.0163   1.0000   0.8792
  -0.500  -0.1738   0.02189   0.01175   0.0165   1.0000   0.8852
  -0.250  -0.1497   0.02172   0.01155   0.0163   1.0000   0.8914
   0.000  -0.1267   0.02150   0.01132   0.0165   1.0000   0.8971
   0.250  -0.1021   0.02139   0.01119   0.0162   1.0000   0.9025
   0.500  -0.0773   0.02129   0.01111   0.0158   1.0000   0.9074
   0.750  -0.0526   0.02122   0.01106   0.0155   1.0000   0.9120
   1.000  -0.0271   0.02122   0.01110   0.0148   1.0000   0.9167
   1.250  -0.0017   0.02124   0.01119   0.0142   1.0000   0.9213
   1.500   0.0232   0.02129   0.01132   0.0136   1.0000   0.9261
   1.750   0.0577   0.02147   0.01160   0.0112   0.9948   0.9304
   2.000   0.1068   0.02172   0.01199   0.0062   0.9793   0.9331
   2.250   0.1547   0.02186   0.01230   0.0017   0.9623   0.9356
   2.500   0.2065   0.02187   0.01252  -0.0031   0.9414   0.9375
   2.750   0.2651   0.02144   0.01234  -0.0078   0.9046   0.9384
   3.000   0.3194   0.02066   0.01181  -0.0107   0.8594   0.9397
   3.250   0.3606   0.01992   0.01125  -0.0110   0.8020   0.9424
   3.500   0.3963   0.01936   0.01070  -0.0101   0.7060   0.9457
   3.750   0.4285   0.01966   0.00999  -0.0082   0.4698   0.9483
   4.000   0.4439   0.02115   0.01038  -0.0062   0.2946   0.9530
   4.250   0.4657   0.02250   0.01114  -0.0061   0.2117   0.9581
   4.500   0.4918   0.02360   0.01200  -0.0064   0.1724   0.9634
   4.750   0.5201   0.02462   0.01292  -0.0070   0.1495   0.9695
   5.000   0.5510   0.02563   0.01395  -0.0079   0.1329   0.9759
   5.250   0.5827   0.02674   0.01507  -0.0089   0.1206   0.9838
   5.500   0.6134   0.02781   0.01623  -0.0097   0.1101   1.0000
   5.750   0.6440   0.02920   0.01776  -0.0103   0.1019   1.0000
   6.000   0.6729   0.03060   0.01916  -0.0111   0.0944   1.0000
   6.250   0.7031   0.03237   0.02123  -0.0118   0.0882   1.0000
   6.500   0.7312   0.03398   0.02296  -0.0125   0.0821   1.0000
   6.750   0.7590   0.03619   0.02541  -0.0131   0.0779   1.0000
   7.000   0.7850   0.03845   0.02816  -0.0135   0.0729   1.0000
   7.250   0.8100   0.04068   0.03061  -0.0139   0.0694   1.0000
   7.500   0.8338   0.04333   0.03335  -0.0145   0.0670   1.0000
   7.750   0.8511   0.04687   0.03768  -0.0142   0.0644   1.0000
   8.000   0.8661   0.05047   0.04183  -0.0140   0.0618   1.0000
   8.250   0.8784   0.05431   0.04616  -0.0139   0.0603   1.0000
   8.500   0.8866   0.05856   0.05084  -0.0137   0.0596   1.0000
   8.750   0.8899   0.06315   0.05583  -0.0137   0.0591   1.0000
   9.000   0.8880   0.06804   0.06107  -0.0139   0.0588   1.0000
   9.250   0.8802   0.07320   0.06654  -0.0144   0.0586   1.0000
   9.500   0.8634   0.07886   0.07245  -0.0154   0.0588   1.0000
   9.750   0.8372   0.08594   0.07971  -0.0186   0.0596   1.0000
  10.000   0.8118   0.09523   0.08910  -0.0259   0.0607   1.0000
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