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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 500,000
Max Cl/Cd: 50.18 at α=0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20503-il-500000.txt
Download as CSV file: xf-sc20503-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6500   0.09687   0.09466   0.0178   1.0000   0.0084
  -8.250  -0.6462   0.09302   0.09082   0.0155   1.0000   0.0086
  -8.000  -0.6424   0.08912   0.08695   0.0129   1.0000   0.0088
  -7.750  -0.6343   0.08469   0.08253   0.0083   1.0000   0.0090
  -7.500  -0.6220   0.07968   0.07748   0.0018   1.0000   0.0092
  -7.250  -0.6060   0.07425   0.07203  -0.0055   1.0000   0.0095
  -7.000  -0.5867   0.06894   0.06665  -0.0122   1.0000   0.0098
  -6.750  -0.5642   0.06413   0.06176  -0.0176   1.0000   0.0102
  -6.500  -0.5413   0.05978   0.05730  -0.0215   1.0000   0.0105
  -6.250  -0.5187   0.05534   0.05272  -0.0247   1.0000   0.0106
  -6.000  -0.4956   0.05092   0.04814  -0.0274   1.0000   0.0107
  -5.750  -0.4716   0.04661   0.04364  -0.0296   1.0000   0.0107
  -5.500  -0.4465   0.04243   0.03924  -0.0315   1.0000   0.0108
  -5.250  -0.4204   0.03842   0.03498  -0.0331   1.0000   0.0108
  -5.000  -0.3926   0.03151   0.02767  -0.0360   1.0000   0.0113
  -4.750  -0.3642   0.02606   0.02185  -0.0386   1.0000   0.0125
  -4.500  -0.3358   0.02325   0.01881  -0.0397   1.0000   0.0137
  -4.250  -0.3059   0.02077   0.01604  -0.0405   1.0000   0.0152
  -4.000  -0.2753   0.01853   0.01347  -0.0409   1.0000   0.0169
  -3.750  -0.2445   0.01637   0.01090  -0.0411   1.0000   0.0178
  -3.250  -0.1825   0.01157   0.00549  -0.0403   1.0000   0.0086
  -3.000  -0.1524   0.00994   0.00371  -0.0405   1.0000   0.0083
  -2.750  -0.1223   0.00893   0.00259  -0.0409   1.0000   0.0099
  -2.500  -0.0921   0.00811   0.00169  -0.0414   1.0000   0.0175
  -2.250  -0.0547   0.00559   0.00101  -0.0452   1.0000   0.5783
  -2.000  -0.0278   0.00517   0.00105  -0.0450   1.0000   0.7291
  -1.750  -0.0032   0.00500   0.00111  -0.0440   1.0000   0.8042
  -1.500   0.0195   0.00491   0.00114  -0.0425   1.0000   0.8561
  -1.250   0.0430   0.00483   0.00113  -0.0413   1.0000   0.8818
  -1.000   0.0666   0.00476   0.00110  -0.0402   1.0000   0.9021
  -0.750   0.0882   0.00465   0.00106  -0.0387   1.0000   0.9248
  -0.500   0.1062   0.00447   0.00098  -0.0362   1.0000   0.9671
  -0.250   0.1324   0.00447   0.00100  -0.0360   1.0000   1.0000
   0.000   0.1617   0.00450   0.00107  -0.0366   1.0000   1.0000
   0.250   0.1907   0.00454   0.00119  -0.0369   1.0000   1.0000
   0.500   0.2519   0.00502   0.00102  -0.0436   0.7234   1.0000
   0.750   0.2699   0.00818   0.00162  -0.0427   0.0280   1.0000
   1.000   0.2982   0.00891   0.00239  -0.0428   0.0113   1.0000
   1.250   0.3261   0.00978   0.00334  -0.0426   0.0088   1.0000
   1.500   0.3537   0.01104   0.00471  -0.0421   0.0079   1.0000
   1.750   0.3815   0.01293   0.00677  -0.0414   0.0084   1.0000
   2.000   0.4114   0.01513   0.00923  -0.0404   0.0139   1.0000
   2.250   0.4408   0.01773   0.01219  -0.0394   0.0164   1.0000
   2.500   0.4693   0.01987   0.01473  -0.0387   0.0154   1.0000
   2.750   0.4968   0.02210   0.01726  -0.0381   0.0140   1.0000
   3.000   0.5231   0.02453   0.01997  -0.0377   0.0127   1.0000
   3.250   0.5477   0.02734   0.02301  -0.0374   0.0117   1.0000
   3.500   0.5688   0.03252   0.02855  -0.0372   0.0107   1.0000
   3.750   0.5893   0.03890   0.03533  -0.0368   0.0102   1.0000
   4.000   0.6126   0.04267   0.03935  -0.0365   0.0102   1.0000
   4.250   0.6353   0.04659   0.04351  -0.0365   0.0102   1.0000
   4.500   0.6576   0.05066   0.04779  -0.0367   0.0101   1.0000
   4.750   0.6794   0.05481   0.05213  -0.0372   0.0100   1.0000
   5.000   0.7014   0.05891   0.05640  -0.0381   0.0099   1.0000
   5.250   0.7248   0.06270   0.06034  -0.0394   0.0095   1.0000
   5.500   0.7479   0.06702   0.06479  -0.0416   0.0090   1.0000
   5.750   0.7672   0.07193   0.06982  -0.0445   0.0086   1.0000
   6.000   0.7833   0.07707   0.07509  -0.0480   0.0083   1.0000
   6.250   0.7967   0.08230   0.08038  -0.0521   0.0080   1.0000
   6.500   0.8077   0.08755   0.08568  -0.0565   0.0078   1.0000
   6.750   0.8162   0.09273   0.09088  -0.0612   0.0077   1.0000
   7.000   0.8220   0.09777   0.09593  -0.0660   0.0076   1.0000
   7.250   0.8224   0.10228   0.10043  -0.0698   0.0075   1.0000
   7.500   0.8229   0.10663   0.10476  -0.0726   0.0074   1.0000
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