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NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il)
Reynolds number: 100,000
Max Cl/Cd: 30.54 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0011sc-il-100000-n5.txt
Download as CSV file: xf-n0011sc-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA/LANGLEY SYMMETRICAL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6464   0.09955   0.09352  -0.0351   1.0000   0.0410
 -11.750  -0.7467   0.07361   0.06740  -0.0519   1.0000   0.0394
 -11.500  -0.8094   0.06471   0.05817  -0.0530   1.0000   0.0387
 -11.250  -0.8568   0.05942   0.05256  -0.0489   1.0000   0.0384
 -11.000  -0.8802   0.05669   0.04964  -0.0442   1.0000   0.0384
 -10.750  -0.8951   0.05483   0.04767  -0.0393   1.0000   0.0387
 -10.500  -0.9107   0.05308   0.04578  -0.0338   1.0000   0.0390
 -10.250  -0.9212   0.05122   0.04377  -0.0289   1.0000   0.0394
 -10.000  -0.9288   0.04926   0.04163  -0.0242   1.0000   0.0399
  -9.750  -0.9350   0.04724   0.03939  -0.0196   1.0000   0.0405
  -9.500  -0.9403   0.04501   0.03688  -0.0149   1.0000   0.0410
  -9.250  -0.9435   0.04275   0.03428  -0.0103   1.0000   0.0417
  -9.000  -0.9434   0.04052   0.03169  -0.0061   1.0000   0.0423
  -8.750  -0.9396   0.03841   0.02920  -0.0023   1.0000   0.0429
  -8.500  -0.9327   0.03641   0.02683   0.0012   1.0000   0.0436
  -8.250  -0.9199   0.03503   0.02537   0.0035   1.0000   0.0442
  -8.000  -0.9067   0.03387   0.02412   0.0059   1.0000   0.0451
  -7.750  -0.8930   0.03278   0.02291   0.0082   1.0000   0.0463
  -7.500  -0.8784   0.03165   0.02160   0.0105   1.0000   0.0479
  -7.250  -0.8624   0.03042   0.02009   0.0127   1.0000   0.0497
  -7.000  -0.8453   0.02932   0.01893   0.0145   1.0000   0.0511
  -6.750  -0.8283   0.02842   0.01801   0.0163   1.0000   0.0525
  -6.500  -0.8105   0.02752   0.01703   0.0182   1.0000   0.0543
  -6.250  -0.7925   0.02670   0.01605   0.0200   1.0000   0.0570
  -6.000  -0.7751   0.02587   0.01522   0.0219   1.0000   0.0593
  -5.750  -0.7580   0.02518   0.01454   0.0238   1.0000   0.0620
  -5.500  -0.7403   0.02448   0.01375   0.0257   1.0000   0.0650
  -5.250  -0.7234   0.02380   0.01306   0.0277   1.0000   0.0686
  -5.000  -0.7068   0.02321   0.01249   0.0298   1.0000   0.0727
  -4.750  -0.6898   0.02262   0.01185   0.0319   1.0000   0.0774
  -4.500  -0.6738   0.02206   0.01133   0.0341   1.0000   0.0826
  -4.250  -0.6572   0.02154   0.01080   0.0362   1.0000   0.0895
  -4.000  -0.6409   0.02105   0.01035   0.0383   1.0000   0.0974
  -3.750  -0.6246   0.02056   0.00992   0.0405   1.0000   0.1075
  -3.500  -0.6081   0.02010   0.00953   0.0426   1.0000   0.1210
  -3.250  -0.5914   0.01966   0.00918   0.0447   1.0000   0.1388
  -3.000  -0.5748   0.01922   0.00889   0.0467   1.0000   0.1634
  -2.750  -0.5583   0.01874   0.00863   0.0487   1.0000   0.2009
  -2.500  -0.5333   0.01821   0.00848   0.0488   0.9975   0.2688
  -2.250  -0.5074   0.01749   0.00843   0.0487   0.9943   0.3930
  -2.000  -0.3926   0.01698   0.00994   0.0329   1.0000   0.8201
  -1.750  -0.3415   0.01785   0.01077   0.0293   1.0000   0.8779
  -1.500  -0.3097   0.01848   0.01132   0.0290   1.0000   0.9081
  -1.250  -0.2759   0.01912   0.01188   0.0283   1.0000   0.9326
  -1.000  -0.2242   0.01981   0.01247   0.0238   1.0000   0.9498
  -0.750  -0.1589   0.02055   0.01314   0.0165   1.0000   0.9690
  -0.500  -0.0836   0.02107   0.01361   0.0069   1.0000   0.9866
  -0.250  -0.0362   0.02120   0.01370   0.0024   1.0000   0.9949
   0.000   0.0000   0.02126   0.01375   0.0000   1.0000   1.0000
   0.250   0.0360   0.02119   0.01370  -0.0024   0.9950   1.0000
   0.500   0.0845   0.02107   0.01360  -0.0071   0.9864   1.0000
   0.750   0.1591   0.02054   0.01313  -0.0165   0.9689   1.0000
   1.000   0.2248   0.01979   0.01246  -0.0239   0.9497   1.0000
   1.250   0.2757   0.01912   0.01187  -0.0282   0.9324   1.0000
   1.500   0.3097   0.01847   0.01131  -0.0290   0.9081   1.0000
   1.750   0.3415   0.01785   0.01077  -0.0293   0.8781   1.0000
   2.000   0.3869   0.01706   0.01003  -0.0319   0.8256   1.0000
   2.250   0.5074   0.01747   0.00843  -0.0487   0.3956   0.9943
   2.500   0.5334   0.01821   0.00848  -0.0489   0.2693   0.9975
   2.750   0.5583   0.01874   0.00863  -0.0487   0.2010   1.0000
   3.000   0.5747   0.01921   0.00888  -0.0467   0.1642   1.0000
   3.250   0.5914   0.01966   0.00918  -0.0447   0.1388   1.0000
   3.500   0.6080   0.02009   0.00952  -0.0426   0.1210   1.0000
   3.750   0.6245   0.02056   0.00992  -0.0405   0.1075   1.0000
   4.000   0.6408   0.02104   0.01034  -0.0384   0.0974   1.0000
   4.250   0.6571   0.02154   0.01080  -0.0362   0.0892   1.0000
   4.500   0.6737   0.02206   0.01133  -0.0340   0.0826   1.0000
   4.750   0.6896   0.02263   0.01185  -0.0319   0.0773   1.0000
   5.000   0.7067   0.02321   0.01249  -0.0298   0.0728   1.0000
   5.250   0.7233   0.02379   0.01305  -0.0277   0.0685   1.0000
   5.500   0.7402   0.02448   0.01375  -0.0257   0.0652   1.0000
   5.750   0.7579   0.02518   0.01453  -0.0238   0.0619   1.0000
   6.000   0.7750   0.02588   0.01522  -0.0219   0.0593   1.0000
   6.250   0.7924   0.02668   0.01605  -0.0200   0.0568   1.0000
   6.500   0.8105   0.02753   0.01703  -0.0182   0.0542   1.0000
   6.750   0.8280   0.02840   0.01799  -0.0163   0.0524   1.0000
   7.000   0.8451   0.02931   0.01890  -0.0145   0.0510   1.0000
   7.250   0.8622   0.03043   0.02013  -0.0126   0.0494   1.0000
   7.500   0.8781   0.03162   0.02158  -0.0105   0.0477   1.0000
   7.750   0.8928   0.03274   0.02287  -0.0082   0.0462   1.0000
   8.000   0.9065   0.03382   0.02405  -0.0058   0.0449   1.0000
   8.250   0.9198   0.03502   0.02534  -0.0035   0.0441   1.0000
   8.500   0.9326   0.03643   0.02683  -0.0012   0.0435   1.0000
   8.750   0.9389   0.03848   0.02930   0.0024   0.0427   1.0000
   9.000   0.9429   0.04057   0.03176   0.0062   0.0422   1.0000
   9.250   0.9432   0.04280   0.03434   0.0104   0.0417   1.0000
   9.500   0.9403   0.04503   0.03691   0.0149   0.0410   1.0000
   9.750   0.9347   0.04730   0.03945   0.0196   0.0405   1.0000
  10.000   0.9277   0.04940   0.04179   0.0243   0.0399   1.0000
  10.250   0.9175   0.05162   0.04422   0.0293   0.0396   1.0000
  10.500   0.9043   0.05360   0.04637   0.0346   0.0392   1.0000
  10.750   0.8929   0.05502   0.04788   0.0396   0.0387   1.0000
  11.000   0.8736   0.05718   0.05019   0.0448   0.0386   1.0000
  11.250   0.8456   0.06033   0.05356   0.0496   0.0386   1.0000
  11.500   0.8154   0.06417   0.05759   0.0528   0.0386   1.0000
  11.750   0.7381   0.07500   0.06883   0.0510   0.0395   1.0000
  12.000   0.6477   0.09944   0.09341   0.0352   0.0416   1.0000
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