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SA7038 (sa7038-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 100,000
Max Cl/Cd: 56.2 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7038-il-100000.txt
Download as CSV file: xf-sa7038-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7038                                          
  
 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  -0.3531   0.10442   0.09947  -0.0308   1.0000   0.0835
  -8.750  -0.3671   0.10310   0.09828  -0.0345   1.0000   0.0858
  -8.500  -0.3812   0.10161   0.09691  -0.0369   1.0000   0.0862
  -8.250  -0.3533   0.09552   0.09078  -0.0325   1.0000   0.0900
  -8.000  -0.3500   0.09291   0.08822  -0.0317   1.0000   0.0929
  -7.750  -0.3545   0.09063   0.08603  -0.0315   1.0000   0.0960
  -7.500  -0.3704   0.08914   0.08468  -0.0312   1.0000   0.0984
  -7.250  -0.3964   0.08800   0.08369  -0.0328   1.0000   0.0997
  -7.000  -0.4180   0.08577   0.08148  -0.0388   1.0000   0.1003
  -6.750  -0.4015   0.08165   0.07747  -0.0295   1.0000   0.1029
  -6.500  -0.3996   0.07940   0.07527  -0.0267   1.0000   0.1058
  -6.250  -0.4042   0.07695   0.07287  -0.0266   1.0000   0.1093
  -6.000  -0.4188   0.07297   0.06874  -0.0376   1.0000   0.1149
  -5.750  -0.4126   0.07008   0.06601  -0.0315   1.0000   0.1168
  -5.500  -0.4084   0.06784   0.06382  -0.0286   1.0000   0.1208
  -5.250  -0.4043   0.06349   0.05929  -0.0351   1.0000   0.1300
  -5.000  -0.3982   0.06118   0.05708  -0.0315   1.0000   0.1332
  -4.750  -0.3875   0.05749   0.05322  -0.0351   1.0000   0.1449
  -4.500  -0.3786   0.05527   0.05105  -0.0328   1.0000   0.1497
  -4.250  -0.3651   0.05207   0.04775  -0.0344   1.0000   0.1617
  -4.000  -0.3502   0.04929   0.04487  -0.0353   1.0000   0.1755
  -3.750  -0.2832   0.03456   0.02818  -0.0469   1.0000   0.0752
  -3.500  -0.2554   0.03101   0.02415  -0.0473   1.0000   0.0652
  -3.250  -0.2276   0.02825   0.02074  -0.0476   1.0000   0.0629
  -3.000  -0.1988   0.02636   0.01843  -0.0480   0.9990   0.0633
  -2.750  -0.1535   0.02430   0.01584  -0.0509   0.9935   0.0626
  -2.500  -0.1106   0.02283   0.01412  -0.0536   0.9868   0.0643
  -2.250  -0.0678   0.02171   0.01286  -0.0561   0.9799   0.0695
  -2.000  -0.0246   0.02074   0.01192  -0.0590   0.9725   0.0850
  -1.500   0.0415   0.01675   0.01111  -0.0603   0.9589   0.7589
  -1.250   0.0915   0.01649   0.01079  -0.0640   0.9492   1.0000
  -1.000   0.1368   0.01675   0.01068  -0.0675   0.9397   1.0000
  -0.750   0.1821   0.01693   0.01056  -0.0710   0.9300   1.0000
  -0.500   0.2207   0.01707   0.01047  -0.0731   0.9184   1.0000
  -0.250   0.2611   0.01716   0.01038  -0.0755   0.9074   1.0000
   0.000   0.3135   0.01710   0.01013  -0.0800   0.9003   1.0000
   0.250   0.3513   0.01707   0.00998  -0.0816   0.8881   1.0000
   0.500   0.3888   0.01699   0.00980  -0.0831   0.8762   1.0000
   0.750   0.4267   0.01685   0.00957  -0.0845   0.8649   1.0000
   1.000   0.4669   0.01658   0.00923  -0.0861   0.8550   1.0000
   1.250   0.5039   0.01630   0.00890  -0.0869   0.8440   1.0000
   1.500   0.5354   0.01610   0.00865  -0.0869   0.8306   1.0000
   1.750   0.5666   0.01588   0.00839  -0.0866   0.8169   1.0000
   2.000   0.5971   0.01566   0.00814  -0.0862   0.8027   1.0000
   2.250   0.6272   0.01543   0.00787  -0.0857   0.7879   1.0000
   2.500   0.6567   0.01523   0.00762  -0.0851   0.7725   1.0000
   2.750   0.6827   0.01519   0.00755  -0.0840   0.7538   1.0000
   3.000   0.7099   0.01512   0.00747  -0.0831   0.7352   1.0000
   3.250   0.7378   0.01506   0.00734  -0.0823   0.7169   1.0000
   3.500   0.7637   0.01513   0.00736  -0.0813   0.6962   1.0000
   3.750   0.7900   0.01521   0.00738  -0.0804   0.6753   1.0000
   4.000   0.8154   0.01537   0.00751  -0.0794   0.6532   1.0000
   4.250   0.8411   0.01555   0.00761  -0.0785   0.6311   1.0000
   4.500   0.8654   0.01580   0.00782  -0.0774   0.6072   1.0000
   4.750   0.8904   0.01606   0.00800  -0.0765   0.5843   1.0000
   5.000   0.9146   0.01637   0.00829  -0.0755   0.5601   1.0000
   5.250   0.9381   0.01673   0.00861  -0.0744   0.5355   1.0000
   5.500   0.9618   0.01712   0.00892  -0.0734   0.5113   1.0000
   5.750   0.9852   0.01753   0.00926  -0.0723   0.4870   1.0000
   6.000   1.0076   0.01799   0.00973  -0.0712   0.4614   1.0000
   6.250   1.0298   0.01848   0.01019  -0.0701   0.4364   1.0000
   6.500   1.0521   0.01902   0.01065  -0.0690   0.4124   1.0000
   6.750   1.0736   0.01959   0.01119  -0.0679   0.3879   1.0000
   7.000   1.0947   0.02022   0.01185  -0.0667   0.3637   1.0000
   7.250   1.1157   0.02090   0.01246  -0.0655   0.3405   1.0000
   7.500   1.1359   0.02161   0.01315  -0.0643   0.3173   1.0000
   7.750   1.1553   0.02236   0.01391  -0.0630   0.2942   1.0000
   8.000   1.1746   0.02318   0.01463  -0.0617   0.2726   1.0000
   8.250   1.1920   0.02399   0.01555  -0.0602   0.2498   1.0000
   8.500   1.2099   0.02492   0.01638  -0.0588   0.2295   1.0000
   8.750   1.2260   0.02587   0.01743  -0.0572   0.2086   1.0000
   9.000   1.2420   0.02694   0.01843  -0.0556   0.1896   1.0000
   9.250   1.2562   0.02809   0.01965  -0.0538   0.1707   1.0000
   9.500   1.2698   0.02935   0.02095  -0.0519   0.1529   1.0000
   9.750   1.2824   0.03069   0.02225  -0.0501   0.1366   1.0000
  10.000   1.2957   0.03230   0.02386  -0.0483   0.1220   1.0000
  10.250   1.3075   0.03393   0.02554  -0.0464   0.1091   1.0000
  10.500   1.3178   0.03563   0.02739  -0.0443   0.0979   1.0000
  10.750   1.3284   0.03766   0.02958  -0.0423   0.0880   1.0000
  11.000   1.3352   0.03956   0.03153  -0.0401   0.0791   1.0000
  11.250   1.3413   0.04154   0.03337  -0.0381   0.0700   1.0000
  11.500   1.3350   0.04312   0.03537  -0.0344   0.0642   1.0000
  11.750   1.3382   0.04557   0.03777  -0.0325   0.0574   1.0000
  12.000   1.3330   0.04792   0.04048  -0.0298   0.0526   1.0000
  12.250   1.3376   0.05101   0.04344  -0.0286   0.0471   1.0000
  12.500   1.3290   0.05396   0.04682  -0.0264   0.0448   1.0000
  12.750   1.3235   0.05749   0.05072  -0.0249   0.0427   1.0000
  13.000   1.3162   0.06119   0.05469  -0.0239   0.0411   1.0000
  13.250   1.3083   0.06502   0.05873  -0.0233   0.0398   1.0000
  13.500   1.3009   0.06916   0.06303  -0.0231   0.0387   1.0000
  13.750   1.2897   0.07395   0.06803  -0.0235   0.0382   1.0000
  14.000   1.2744   0.07939   0.07369  -0.0245   0.0378   1.0000
  14.250   1.2551   0.08530   0.07986  -0.0264   0.0377   1.0000
  14.500   1.2316   0.09192   0.08677  -0.0297   0.0380   1.0000
  14.750   1.1902   0.10239   0.09764  -0.0366   0.0398   1.0000
  15.000   1.1365   0.11770   0.11330  -0.0476   0.0432   1.0000
  15.250   1.1042   0.13024   0.12595  -0.0560   0.0453   1.0000
  15.500   1.0812   0.14144   0.13717  -0.0628   0.0467   1.0000
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