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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 200,000
Max Cl/Cd: 32.1 at α=0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20503-il-200000-n5.txt
Download as CSV file: xf-sc20503-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6397   0.10492   0.10137   0.0147   1.0000   0.0134
  -8.500  -0.6353   0.10098   0.09745   0.0124   1.0000   0.0134
  -8.250  -0.6308   0.09697   0.09348   0.0098   1.0000   0.0135
  -8.000  -0.6234   0.09257   0.08909   0.0058   1.0000   0.0135
  -7.750  -0.6127   0.08764   0.08417   0.0002   1.0000   0.0135
  -7.500  -0.6000   0.08251   0.07902  -0.0054   1.0000   0.0135
  -7.250  -0.5862   0.07748   0.07393  -0.0101   1.0000   0.0135
  -7.000  -0.5712   0.07251   0.06888  -0.0144   1.0000   0.0135
  -6.750  -0.5547   0.06762   0.06388  -0.0180   1.0000   0.0135
  -6.500  -0.5368   0.06280   0.05894  -0.0213   1.0000   0.0135
  -6.250  -0.5223   0.05551   0.05152  -0.0255   1.0000   0.0140
  -6.000  -0.5036   0.04961   0.04541  -0.0287   1.0000   0.0144
  -5.750  -0.4807   0.04476   0.04032  -0.0312   1.0000   0.0147
  -5.500  -0.4540   0.04081   0.03609  -0.0328   1.0000   0.0144
  -5.000  -0.4023   0.03237   0.02711  -0.0363   1.0000   0.0104
  -4.750  -0.3714   0.02829   0.02260  -0.0377   1.0000   0.0091
  -4.500  -0.3394   0.02459   0.01842  -0.0385   1.0000   0.0080
  -4.250  -0.3074   0.02127   0.01458  -0.0389   1.0000   0.0073
  -4.000  -0.2762   0.01849   0.01131  -0.0389   1.0000   0.0067
  -3.750  -0.2465   0.01653   0.00874  -0.0386   1.0000   0.0058
  -3.500  -0.2177   0.01472   0.00667  -0.0385   1.0000   0.0058
  -3.250  -0.1889   0.01306   0.00484  -0.0386   1.0000   0.0061
  -3.000  -0.1595   0.01184   0.00348  -0.0389   1.0000   0.0070
  -2.750  -0.1312   0.01127   0.00285  -0.0391   1.0000   0.0119
  -2.500  -0.1016   0.01048   0.00196  -0.0395   1.0000   0.0293
  -2.250  -0.0698   0.00778   0.00164  -0.0421   1.0000   0.6479
  -2.000  -0.0537   0.00740   0.00179  -0.0386   1.0000   0.8157
  -1.750  -0.0347   0.00725   0.00169  -0.0360   1.0000   0.8643
  -1.500  -0.0143   0.00710   0.00152  -0.0341   1.0000   0.8937
  -1.250   0.0063   0.00695   0.00136  -0.0322   1.0000   0.9226
  -1.000   0.0292   0.00678   0.00121  -0.0309   1.0000   0.9667
  -0.750   0.0557   0.00674   0.00115  -0.0309   1.0000   1.0000
  -0.500   0.0845   0.00677   0.00116  -0.0313   1.0000   1.0000
  -0.250   0.1129   0.00680   0.00121  -0.0316   1.0000   1.0000
   0.000   0.1412   0.00684   0.00130  -0.0319   1.0000   1.0000
   0.250   0.1693   0.00689   0.00146  -0.0320   1.0000   1.0000
   0.500   0.1972   0.00694   0.00163  -0.0322   1.0000   1.0000
   0.750   0.2250   0.00701   0.00186  -0.0323   1.0000   1.0000
   1.000   0.2838   0.01093   0.00240  -0.0389   0.0218   1.0000
   1.250   0.3117   0.01154   0.00304  -0.0389   0.0091   1.0000
   1.500   0.3393   0.01234   0.00394  -0.0387   0.0065   1.0000
   1.750   0.3662   0.01368   0.00540  -0.0383   0.0058   1.0000
   2.000   0.3933   0.01540   0.00728  -0.0378   0.0056   1.0000
   2.250   0.4213   0.01723   0.00937  -0.0373   0.0056   1.0000
   2.500   0.4505   0.01919   0.01193  -0.0365   0.0065   1.0000
   2.750   0.4794   0.02188   0.01508  -0.0356   0.0071   1.0000
   3.000   0.5080   0.02499   0.01868  -0.0346   0.0079   1.0000
   3.250   0.5356   0.02837   0.02251  -0.0338   0.0088   1.0000
   3.500   0.5620   0.03202   0.02658  -0.0331   0.0100   1.0000
   3.750   0.5854   0.03633   0.03126  -0.0328   0.0117   1.0000
   4.000   0.6060   0.04031   0.03544  -0.0329   0.0140   1.0000
   4.250   0.6313   0.04352   0.03894  -0.0326   0.0144   1.0000
   4.500   0.6522   0.04794   0.04364  -0.0328   0.0142   1.0000
   4.750   0.6692   0.05353   0.04947  -0.0335   0.0138   1.0000
   5.000   0.6821   0.06075   0.05688  -0.0349   0.0133   1.0000
   5.250   0.7000   0.06540   0.06172  -0.0360   0.0133   1.0000
   5.500   0.7166   0.07014   0.06663  -0.0375   0.0133   1.0000
   5.750   0.7320   0.07500   0.07162  -0.0393   0.0133   1.0000
   6.000   0.7460   0.07992   0.07666  -0.0415   0.0132   1.0000
   6.250   0.7586   0.08490   0.08173  -0.0442   0.0132   1.0000
   6.500   0.7697   0.08990   0.08681  -0.0473   0.0132   1.0000
   6.750   0.7794   0.09490   0.09186  -0.0508   0.0132   1.0000
   7.000   0.7875   0.09987   0.09686  -0.0547   0.0132   1.0000
   7.250   0.7936   0.10473   0.10173  -0.0588   0.0132   1.0000
   7.500   0.7962   0.10926   0.10625  -0.0626   0.0131   1.0000
   7.750   0.7986   0.11368   0.11064  -0.0657   0.0131   1.0000
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