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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 50,000
Max Cl/Cd: 19.38 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20503-il-50000-n5.txt
Download as CSV file: xf-sc20503-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6668   0.11682   0.10986   0.0200   1.0000   0.0756
  -9.000  -0.6715   0.11447   0.10762   0.0148   1.0000   0.0776
  -8.750  -0.6741   0.11158   0.10483   0.0091   1.0000   0.0781
  -8.500  -0.6589   0.10521   0.09843   0.0145   1.0000   0.0813
  -8.250  -0.6541   0.10137   0.09463   0.0133   1.0000   0.0843
  -8.000  -0.6511   0.09761   0.09093   0.0086   1.0000   0.0887
  -7.750  -0.6462   0.09295   0.08633   0.0001   1.0000   0.0921
  -7.500  -0.6366   0.08850   0.08190   0.0014   1.0000   0.0949
  -7.250  -0.6264   0.08407   0.07746  -0.0019   1.0000   0.0985
  -7.000  -0.6161   0.07924   0.07260  -0.0081   1.0000   0.1066
  -6.500  -0.5643   0.06620   0.05905  -0.0187   1.0000   0.0369
  -6.250  -0.5476   0.06133   0.05407  -0.0212   1.0000   0.0338
  -6.000  -0.5259   0.05638   0.04887  -0.0246   1.0000   0.0321
  -5.750  -0.5018   0.05167   0.04385  -0.0277   1.0000   0.0318
  -5.500  -0.4758   0.04731   0.03910  -0.0304   1.0000   0.0331
  -5.250  -0.4476   0.04322   0.03454  -0.0327   1.0000   0.0348
  -5.000  -0.4178   0.03939   0.03015  -0.0346   1.0000   0.0360
  -4.750  -0.3877   0.03575   0.02597  -0.0358   1.0000   0.0359
  -4.500  -0.3574   0.03234   0.02202  -0.0366   1.0000   0.0347
  -4.250  -0.3270   0.02933   0.01847  -0.0369   1.0000   0.0340
  -4.000  -0.2973   0.02674   0.01496  -0.0366   1.0000   0.0335
  -3.750  -0.2692   0.02450   0.01232  -0.0357   1.0000   0.0347
  -3.500  -0.2429   0.02263   0.01013  -0.0343   1.0000   0.0369
  -3.250  -0.2180   0.02091   0.00821  -0.0331   1.0000   0.0424
  -3.000  -0.1907   0.01950   0.00664  -0.0330   1.0000   0.0619
  -2.750  -0.1607   0.01780   0.00485  -0.0333   1.0000   0.0911
  -2.500  -0.1634   0.01409   0.00465  -0.0255   1.0000   0.8300
  -2.250  -0.1399   0.01338   0.00362  -0.0226   1.0000   1.0000
  -2.000  -0.1118   0.01330   0.00306  -0.0229   1.0000   1.0000
  -1.750  -0.0838   0.01324   0.00265  -0.0233   1.0000   1.0000
  -1.500  -0.0561   0.01320   0.00235  -0.0235   1.0000   1.0000
  -1.250  -0.0284   0.01318   0.00204  -0.0237   1.0000   1.0000
  -1.000  -0.0009   0.01317   0.00187  -0.0239   1.0000   1.0000
  -0.750   0.0264   0.01318   0.00177  -0.0240   1.0000   1.0000
  -0.500   0.0536   0.01319   0.00175  -0.0241   1.0000   1.0000
  -0.250   0.0806   0.01323   0.00179  -0.0242   1.0000   1.0000
   0.000   0.1076   0.01327   0.00191  -0.0242   1.0000   1.0000
   0.250   0.1344   0.01333   0.00209  -0.0242   1.0000   1.0000
   0.500   0.1613   0.01340   0.00243  -0.0241   1.0000   1.0000
   0.750   0.1880   0.01348   0.00274  -0.0240   1.0000   1.0000
   1.000   0.2146   0.01358   0.00314  -0.0239   1.0000   1.0000
   1.250   0.2413   0.01370   0.00368  -0.0237   1.0000   1.0000
   1.500   0.2682   0.01384   0.00446  -0.0234   1.0000   1.0000
   1.750   0.3357   0.01972   0.00692  -0.0296   0.0601   1.0000
   2.000   0.3633   0.02124   0.00856  -0.0294   0.0402   1.0000
   2.250   0.3936   0.02311   0.01075  -0.0289   0.0358   1.0000
   2.500   0.4236   0.02522   0.01320  -0.0282   0.0337   1.0000
   2.750   0.4536   0.02761   0.01643  -0.0274   0.0333   1.0000
   3.000   0.4830   0.03028   0.01962  -0.0268   0.0336   1.0000
   3.250   0.5117   0.03327   0.02313  -0.0262   0.0344   1.0000
   3.500   0.5393   0.03651   0.02689  -0.0258   0.0353   1.0000
   3.750   0.5661   0.03984   0.03078  -0.0255   0.0349   1.0000
   4.000   0.5920   0.04330   0.03477  -0.0254   0.0332   1.0000
   4.250   0.6161   0.04695   0.03888  -0.0257   0.0310   1.0000
   4.500   0.6385   0.05085   0.04316  -0.0262   0.0296   1.0000
   4.750   0.6608   0.05527   0.04796  -0.0270   0.0305   1.0000
   5.000   0.6816   0.06003   0.05305  -0.0283   0.0330   1.0000
   5.250   0.6981   0.06493   0.05811  -0.0293   0.0365   1.0000
   6.250   0.7734   0.08690   0.08099  -0.0415   0.0949   1.0000
   6.500   0.7836   0.09187   0.08594  -0.0405   0.0917   1.0000
   6.750   0.7878   0.09651   0.09066  -0.0480   0.0867   1.0000
   7.000   0.7933   0.10101   0.09517  -0.0517   0.0828   1.0000
   7.250   0.8002   0.10562   0.09978  -0.0522   0.0797   1.0000
   7.500   0.8093   0.11171   0.10581  -0.0489   0.0776   1.0000
   7.750   0.8067   0.11533   0.10941  -0.0567   0.0769   1.0000
   8.000   0.8020   0.11868   0.11268  -0.0631   0.0745   1.0000
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