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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 50,000
Max Cl/Cd: 19.39 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20503-il-50000.txt
Download as CSV file: xf-sc20503-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6764   0.10599   0.09937   0.0173   1.0000   0.1789
  -8.000  -0.6692   0.10172   0.09514   0.0173   1.0000   0.1916
  -7.750  -0.6652   0.09795   0.09142   0.0152   1.0000   0.2050
  -7.500  -0.6532   0.09344   0.08694   0.0192   1.0000   0.2266
  -7.250  -0.6542   0.09037   0.08394   0.0135   1.0000   0.2448
  -7.000  -0.6416   0.08623   0.07984   0.0201   1.0000   0.2774
  -6.750  -0.6395   0.08326   0.07694   0.0188   1.0000   0.3104
  -6.250  -0.6181   0.07638   0.07014   0.0301   1.0000   0.3983
  -6.000  -0.6079   0.07329   0.06709   0.0359   1.0000   0.4524
  -5.750  -0.5938   0.07013   0.06396   0.0431   1.0000   0.5194
  -4.750  -0.4105   0.03866   0.02974  -0.0374   1.0000   0.1515
  -4.500  -0.3718   0.03416   0.02449  -0.0390   1.0000   0.1184
  -4.250  -0.3335   0.03119   0.02046  -0.0396   1.0000   0.0999
  -4.000  -0.3030   0.02781   0.01646  -0.0394   1.0000   0.0930
  -3.750  -0.2716   0.02537   0.01344  -0.0387   1.0000   0.0895
  -3.500  -0.2439   0.02326   0.01114  -0.0378   1.0000   0.0971
  -3.250  -0.2187   0.02141   0.00920  -0.0362   1.0000   0.1112
  -3.000  -0.1927   0.01961   0.00732  -0.0345   1.0000   0.1237
  -2.750  -0.1630   0.01746   0.00543  -0.0345   1.0000   0.1748
  -2.500  -0.1688   0.01347   0.00467  -0.0227   1.0000   1.0000
  -2.250  -0.1399   0.01338   0.00368  -0.0226   1.0000   1.0000
  -2.000  -0.1118   0.01330   0.00311  -0.0229   1.0000   1.0000
  -1.750  -0.0839   0.01324   0.00269  -0.0232   1.0000   1.0000
  -1.500  -0.0561   0.01320   0.00238  -0.0235   1.0000   1.0000
  -1.250  -0.0285   0.01318   0.00210  -0.0237   1.0000   1.0000
  -1.000  -0.0010   0.01317   0.00193  -0.0239   1.0000   1.0000
  -0.750   0.0263   0.01318   0.00183  -0.0240   1.0000   1.0000
  -0.500   0.0535   0.01320   0.00180  -0.0241   1.0000   1.0000
  -0.250   0.0806   0.01323   0.00185  -0.0242   1.0000   1.0000
   0.000   0.1076   0.01327   0.00196  -0.0242   1.0000   1.0000
   0.250   0.1344   0.01333   0.00214  -0.0242   1.0000   1.0000
   0.500   0.1612   0.01340   0.00239  -0.0241   1.0000   1.0000
   0.750   0.1879   0.01349   0.00278  -0.0240   1.0000   1.0000
   1.000   0.2146   0.01359   0.00319  -0.0239   1.0000   1.0000
   1.250   0.2413   0.01371   0.00373  -0.0237   1.0000   1.0000
   1.500   0.2683   0.01384   0.00454  -0.0233   1.0000   1.0000
   1.750   0.3381   0.01976   0.00755  -0.0283   0.1213   1.0000
   2.000   0.3697   0.02176   0.00968  -0.0276   0.1086   1.0000
   2.250   0.4013   0.02391   0.01197  -0.0271   0.0951   1.0000
   2.500   0.4317   0.02628   0.01452  -0.0266   0.0882   1.0000
   2.750   0.4640   0.02879   0.01765  -0.0257   0.0928   1.0000
   3.000   0.4954   0.03182   0.02147  -0.0249   0.1013   1.0000
   3.250   0.5294   0.03502   0.02556  -0.0242   0.1199   1.0000
   3.500   0.5648   0.03899   0.03026  -0.0239   0.1537   1.0000
   4.000   0.6439   0.05641   0.05072  -0.1061   0.7869   1.0000
   4.250   0.6157   0.05827   0.05244  -0.1046   0.8304   1.0000
   4.500   0.6439   0.06308   0.05727  -0.1068   0.7951   1.0000
   5.250   0.7782   0.07714   0.07172  -0.0683   0.3886   1.0000
   6.000   0.7942   0.08804   0.08243  -0.0568   0.2557   1.0000
   6.250   0.7996   0.09214   0.08650  -0.0563   0.2293   1.0000
   6.500   0.8107   0.09704   0.09133  -0.0520   0.2047   1.0000
   6.750   0.8136   0.10118   0.09547  -0.0550   0.1910   1.0000
   7.000   0.8192   0.10579   0.10006  -0.0558   0.1780   1.0000
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