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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 100,000
Max Cl/Cd: 26.54 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20503-il-100000.txt
Download as CSV file: xf-sc20503-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0503 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6698   0.11912   0.11421   0.0188   1.0000   0.0472
  -9.250  -0.6689   0.11616   0.11131   0.0147   1.0000   0.0475
  -9.000  -0.6680   0.11297   0.10818   0.0104   1.0000   0.0477
  -8.750  -0.6643   0.10921   0.10446   0.0046   1.0000   0.0479
  -8.500  -0.6533   0.10168   0.09690   0.0151   1.0000   0.0513
  -8.250  -0.6490   0.09794   0.09307   0.0138   1.0000   0.0534
  -8.000  -0.6454   0.09418   0.08936   0.0114   1.0000   0.0554
  -7.750  -0.6384   0.08990   0.08511   0.0061   1.0000   0.0578
  -7.500  -0.6245   0.08485   0.08002  -0.0058   1.0000   0.0600
  -7.250  -0.6063   0.08078   0.07565  -0.0180   1.0000   0.0609
  -7.000  -0.6047   0.07472   0.06989  -0.0109   1.0000   0.0640
  -6.750  -0.5913   0.07051   0.06564  -0.0132   1.0000   0.0687
  -6.500  -0.5640   0.06541   0.06007  -0.0251   1.0000   0.0746
  -6.250  -0.5557   0.06070   0.05560  -0.0220   1.0000   0.0792
  -6.000  -0.5309   0.05583   0.05040  -0.0280   1.0000   0.0890
  -5.750  -0.5079   0.05178   0.04608  -0.0311   1.0000   0.1016
  -5.500  -0.4878   0.04758   0.04182  -0.0325   1.0000   0.1156
  -5.250  -0.4651   0.04429   0.03838  -0.0339   1.0000   0.1379
  -4.250  -0.3250   0.02758   0.01947  -0.0401   1.0000   0.0707
  -4.000  -0.2890   0.02454   0.01553  -0.0395   1.0000   0.0492
  -3.750  -0.2605   0.02190   0.01253  -0.0398   1.0000   0.0549
  -3.500  -0.2301   0.01961   0.00982  -0.0391   1.0000   0.0517
  -3.250  -0.2013   0.01769   0.00766  -0.0382   1.0000   0.0503
  -3.000  -0.1738   0.01591   0.00592  -0.0376   1.0000   0.0536
  -2.750  -0.1457   0.01446   0.00452  -0.0375   1.0000   0.0703
  -2.500  -0.1187   0.01056   0.00317  -0.0378   1.0000   0.6557
  -2.250  -0.1325   0.00950   0.00286  -0.0244   1.0000   1.0000
  -2.000  -0.1026   0.00945   0.00236  -0.0251   1.0000   1.0000
  -1.750  -0.0732   0.00941   0.00204  -0.0258   1.0000   1.0000
  -1.500  -0.0441   0.00938   0.00181  -0.0264   1.0000   1.0000
  -1.250  -0.0154   0.00938   0.00161  -0.0268   1.0000   1.0000
  -1.000   0.0130   0.00938   0.00150  -0.0272   1.0000   1.0000
  -0.750   0.0412   0.00939   0.00145  -0.0275   1.0000   1.0000
  -0.500   0.0691   0.00942   0.00144  -0.0277   1.0000   1.0000
  -0.250   0.0969   0.00945   0.00149  -0.0279   1.0000   1.0000
   0.000   0.1245   0.00949   0.00160  -0.0281   1.0000   1.0000
   0.250   0.1520   0.00955   0.00175  -0.0281   1.0000   1.0000
   0.500   0.1794   0.00961   0.00201  -0.0282   1.0000   1.0000
   0.750   0.2067   0.00969   0.00228  -0.0282   1.0000   1.0000
   1.000   0.2340   0.00977   0.00265  -0.0281   1.0000   1.0000
   1.250   0.2619   0.00987   0.00334  -0.0278   1.0000   1.0000
   1.500   0.3277   0.01563   0.00568  -0.0339   0.0552   1.0000
   1.750   0.3548   0.01732   0.00733  -0.0332   0.0503   1.0000
   2.000   0.3839   0.01932   0.00941  -0.0325   0.0498   1.0000
   2.250   0.4149   0.02163   0.01212  -0.0314   0.0550   1.0000
   2.500   0.4449   0.02405   0.01494  -0.0307   0.0558   1.0000
   2.750   0.4740   0.02693   0.01843  -0.0301   0.0579   1.0000
   3.000   0.5549   0.03246   0.02657  -0.0314   0.3045   1.0000
   3.250   0.5710   0.03546   0.02953  -0.0291   0.2460   1.0000
   3.750   0.6076   0.04144   0.03555  -0.0276   0.1553   1.0000
   4.000   0.5909   0.02923   0.02407  -0.0232   0.1315   1.0000
   4.250   0.6072   0.03324   0.02811  -0.0229   0.1146   1.0000
   4.750   0.6813   0.05834   0.05275  -0.0283   0.0866   1.0000
   5.250   0.7216   0.06578   0.06101  -0.0327   0.0707   1.0000
   5.500   0.7396   0.07000   0.06544  -0.0351   0.0642   1.0000
   5.750   0.7467   0.07575   0.07096  -0.0327   0.0606   1.0000
   6.000   0.7609   0.08062   0.07612  -0.0371   0.0592   1.0000
   6.250   0.7782   0.08507   0.08082  -0.0448   0.0558   1.0000
   6.500   0.7881   0.08990   0.08570  -0.0488   0.0531   1.0000
   6.750   0.7956   0.09454   0.09047  -0.0516   0.0508   1.0000
   7.000   0.8013   0.09906   0.09499  -0.0498   0.0484   1.0000
   7.250   0.8036   0.10649   0.10229  -0.0452   0.0469   1.0000
   7.500   0.8092   0.11075   0.10662  -0.0509   0.0467   1.0000
   7.750   0.8117   0.11491   0.11080  -0.0572   0.0465   1.0000
   8.000   0.8115   0.11878   0.11462  -0.0627   0.0463   1.0000
   8.250   0.8113   0.12239   0.11819  -0.0675   0.0458   1.0000
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