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SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 50,000
Max Cl/Cd: 37.31 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7080-il-50000-n5.txt
Download as CSV file: xf-sd7080-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7080 (9.2%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4277   0.09786   0.09074  -0.0308   1.0000   0.0568
  -8.750  -0.4232   0.09442   0.08735  -0.0311   1.0000   0.0553
  -8.500  -0.4228   0.09075   0.08375  -0.0320   1.0000   0.0540
  -8.250  -0.4252   0.08705   0.08013  -0.0332   1.0000   0.0527
  -8.000  -0.4306   0.08331   0.07649  -0.0345   1.0000   0.0515
  -7.750  -0.4382   0.07918   0.07248  -0.0366   1.0000   0.0504
  -7.500  -0.4456   0.07413   0.06748  -0.0399   1.0000   0.0490
  -7.250  -0.4559   0.06816   0.06148  -0.0434   1.0000   0.0473
  -7.000  -0.4661   0.06209   0.05505  -0.0464   1.0000   0.0454
  -6.750  -0.4637   0.05842   0.05128  -0.0461   1.0000   0.0451
  -6.500  -0.4596   0.05478   0.04747  -0.0458   1.0000   0.0449
  -6.250  -0.4533   0.05115   0.04361  -0.0455   1.0000   0.0447
  -6.000  -0.4445   0.04754   0.03967  -0.0451   1.0000   0.0447
  -5.750  -0.4329   0.04406   0.03568  -0.0448   1.0000   0.0452
  -5.500  -0.4198   0.04102   0.03240  -0.0442   1.0000   0.0465
  -5.250  -0.4041   0.03875   0.02996  -0.0435   1.0000   0.0482
  -5.000  -0.3865   0.03638   0.02727  -0.0428   1.0000   0.0496
  -4.750  -0.3669   0.03394   0.02442  -0.0421   1.0000   0.0504
  -4.500  -0.3459   0.03171   0.02178  -0.0413   1.0000   0.0513
  -4.250  -0.3241   0.02978   0.01949  -0.0403   1.0000   0.0526
  -4.000  -0.3017   0.02811   0.01749  -0.0393   1.0000   0.0543
  -3.750  -0.2793   0.02669   0.01574  -0.0382   1.0000   0.0564
  -3.500  -0.2575   0.02544   0.01435  -0.0370   1.0000   0.0597
  -3.250  -0.2361   0.02454   0.01339  -0.0361   1.0000   0.0670
  -3.000  -0.2136   0.02362   0.01239  -0.0353   1.0000   0.0756
  -2.750  -0.1909   0.02271   0.01140  -0.0345   1.0000   0.0883
  -2.500  -0.1672   0.02170   0.01057  -0.0342   1.0000   0.1284
  -2.250  -0.1436   0.02029   0.01004  -0.0346   1.0000   0.2681
  -2.000  -0.1246   0.01910   0.00992  -0.0334   1.0000   0.4856
  -1.750  -0.1052   0.01842   0.01014  -0.0304   0.9944   0.7223
  -1.500  -0.0516   0.01806   0.00982  -0.0342   0.9855   1.0000
  -1.250  -0.0095   0.01835   0.00966  -0.0376   0.9749   1.0000
  -1.000   0.0317   0.01864   0.00957  -0.0408   0.9639   1.0000
  -0.750   0.0729   0.01891   0.00951  -0.0439   0.9528   1.0000
  -0.500   0.1150   0.01915   0.00949  -0.0470   0.9416   1.0000
  -0.250   0.1545   0.01934   0.00947  -0.0495   0.9292   1.0000
   0.000   0.1924   0.01950   0.00944  -0.0516   0.9159   1.0000
   0.250   0.2302   0.01962   0.00942  -0.0536   0.9024   1.0000
   0.500   0.2679   0.01972   0.00941  -0.0555   0.8887   1.0000
   0.750   0.3045   0.01977   0.00937  -0.0570   0.8743   1.0000
   1.000   0.3396   0.01979   0.00931  -0.0581   0.8594   1.0000
   1.250   0.3739   0.01977   0.00924  -0.0589   0.8441   1.0000
   1.500   0.4077   0.01971   0.00915  -0.0595   0.8284   1.0000
   1.750   0.4367   0.01971   0.00912  -0.0593   0.8098   1.0000
   2.000   0.4672   0.01967   0.00908  -0.0592   0.7915   1.0000
   2.250   0.4989   0.01959   0.00899  -0.0592   0.7734   1.0000
   2.500   0.5286   0.01956   0.00895  -0.0589   0.7534   1.0000
   2.750   0.5580   0.01954   0.00892  -0.0584   0.7323   1.0000
   3.000   0.5873   0.01954   0.00893  -0.0579   0.7105   1.0000
   3.250   0.6157   0.01959   0.00895  -0.0573   0.6873   1.0000
   3.500   0.6426   0.01972   0.00906  -0.0565   0.6626   1.0000
   3.750   0.6696   0.01988   0.00921  -0.0557   0.6378   1.0000
   4.000   0.6961   0.02009   0.00937  -0.0548   0.6127   1.0000
   4.250   0.7210   0.02039   0.00964  -0.0539   0.5862   1.0000
   4.500   0.7454   0.02074   0.00996  -0.0529   0.5598   1.0000
   4.750   0.7696   0.02113   0.01037  -0.0519   0.5336   1.0000
   5.000   0.7935   0.02156   0.01077  -0.0508   0.5079   1.0000
   5.250   0.8170   0.02203   0.01119  -0.0498   0.4825   1.0000
   5.500   0.8399   0.02255   0.01172  -0.0488   0.4569   1.0000
   5.750   0.8624   0.02312   0.01230  -0.0478   0.4317   1.0000
   6.000   0.8847   0.02371   0.01294  -0.0467   0.4074   1.0000
   6.250   0.9068   0.02435   0.01358  -0.0457   0.3837   1.0000
   6.500   0.9282   0.02504   0.01433  -0.0447   0.3599   1.0000
   6.750   0.9493   0.02577   0.01505  -0.0436   0.3375   1.0000
   7.000   0.9699   0.02655   0.01590  -0.0425   0.3150   1.0000
   7.250   0.9900   0.02737   0.01681  -0.0414   0.2938   1.0000
   7.500   1.0095   0.02826   0.01778  -0.0402   0.2726   1.0000
   7.750   1.0285   0.02919   0.01872  -0.0390   0.2533   1.0000
   8.000   1.0466   0.03021   0.01988  -0.0377   0.2331   1.0000
   8.250   1.0640   0.03127   0.02101  -0.0364   0.2149   1.0000
   8.500   1.0803   0.03239   0.02219  -0.0351   0.1977   1.0000
   8.750   1.0959   0.03365   0.02361  -0.0337   0.1804   1.0000
   9.000   1.1100   0.03496   0.02505  -0.0321   0.1641   1.0000
   9.250   1.1233   0.03638   0.02659  -0.0306   0.1493   1.0000
   9.500   1.1348   0.03790   0.02822  -0.0289   0.1354   1.0000
   9.750   1.1459   0.03961   0.03006  -0.0273   0.1232   1.0000
  10.000   1.1541   0.04138   0.03195  -0.0254   0.1114   1.0000
  10.250   1.1603   0.04324   0.03386  -0.0235   0.1013   1.0000
  10.500   1.1626   0.04519   0.03600  -0.0213   0.0918   1.0000
  10.750   1.1621   0.04748   0.03851  -0.0191   0.0827   1.0000
  11.000   1.1598   0.04979   0.04087  -0.0173   0.0755   1.0000
  11.250   1.1551   0.05240   0.04367  -0.0159   0.0685   1.0000
  11.500   1.1499   0.05541   0.04679  -0.0149   0.0630   1.0000
  11.750   1.1441   0.05879   0.05042  -0.0144   0.0583   1.0000
  12.000   1.1383   0.06198   0.05359  -0.0144   0.0546   1.0000
  12.250   1.1297   0.06643   0.05834  -0.0148   0.0517   1.0000
  12.500   1.1188   0.07136   0.06357  -0.0160   0.0494   1.0000
  12.750   1.1071   0.07654   0.06896  -0.0178   0.0476   1.0000
  13.000   1.0956   0.08199   0.07459  -0.0201   0.0462   1.0000
  13.250   1.0861   0.08724   0.07993  -0.0225   0.0447   1.0000
  13.500   1.0787   0.09230   0.08499  -0.0246   0.0433   1.0000
  13.750   1.0615   0.09992   0.09285  -0.0287   0.0432   1.0000
  14.000   1.0427   0.10831   0.10144  -0.0335   0.0433   1.0000
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