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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 100,000
Max Cl/Cd: 23.96 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20503-il-100000-n5.txt
Download as CSV file: xf-sc20503-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5411   0.08861   0.08394   0.0054   1.0000   0.0312
  -8.250  -0.5413   0.08454   0.07990   0.0041   1.0000   0.0318
  -8.000  -0.5421   0.08044   0.07585   0.0026   1.0000   0.0323
  -7.750  -0.5435   0.07634   0.07178   0.0010   1.0000   0.0327
  -7.500  -0.5445   0.07201   0.06750  -0.0015   1.0000   0.0332
  -7.250  -0.5420   0.06705   0.06255  -0.0058   1.0000   0.0337
  -7.000  -0.5367   0.06170   0.05719  -0.0106   1.0000   0.0342
  -6.750  -0.5285   0.05627   0.05169  -0.0151   1.0000   0.0351
  -6.500  -0.5085   0.05150   0.04647  -0.0242   1.0000   0.0388
  -6.250  -0.4924   0.04680   0.04150  -0.0267   1.0000   0.0390
  -6.000  -0.4810   0.04002   0.03468  -0.0284   1.0000   0.0398
  -5.750  -0.4673   0.03443   0.02915  -0.0278   1.0000   0.0212
  -5.500  -0.4452   0.02928   0.02369  -0.0302   1.0000   0.0181
  -5.000  -0.4039   0.03653   0.02950  -0.0337   1.0000   0.0134
  -4.750  -0.3758   0.03185   0.02440  -0.0355   1.0000   0.0128
  -4.500  -0.3457   0.02825   0.02030  -0.0366   1.0000   0.0124
  -4.250  -0.3153   0.02517   0.01670  -0.0373   1.0000   0.0122
  -4.000  -0.2852   0.02252   0.01353  -0.0375   1.0000   0.0120
  -3.750  -0.2558   0.02016   0.01048  -0.0374   1.0000   0.0116
  -3.500  -0.2277   0.01831   0.00835  -0.0371   1.0000   0.0149
  -3.250  -0.2004   0.01691   0.00684  -0.0371   1.0000   0.0219
  -3.000  -0.1723   0.01543   0.00524  -0.0369   1.0000   0.0244
  -2.750  -0.1431   0.01411   0.00375  -0.0371   1.0000   0.0319
  -2.500  -0.1125   0.01143   0.00256  -0.0389   1.0000   0.3890
  -2.250  -0.1132   0.01008   0.00287  -0.0305   1.0000   0.8516
  -2.000  -0.1025   0.00944   0.00232  -0.0251   1.0000   1.0000
  -1.750  -0.0731   0.00940   0.00201  -0.0258   1.0000   1.0000
  -1.500  -0.0440   0.00938   0.00178  -0.0264   1.0000   1.0000
  -1.250  -0.0153   0.00937   0.00157  -0.0268   1.0000   1.0000
  -1.000   0.0131   0.00938   0.00146  -0.0272   1.0000   1.0000
  -0.750   0.0413   0.00939   0.00140  -0.0275   1.0000   1.0000
  -0.500   0.0692   0.00941   0.00140  -0.0278   1.0000   1.0000
  -0.250   0.0969   0.00945   0.00145  -0.0279   1.0000   1.0000
   0.000   0.1246   0.00949   0.00156  -0.0281   1.0000   1.0000
   0.250   0.1520   0.00954   0.00171  -0.0282   1.0000   1.0000
   0.500   0.1795   0.00961   0.00198  -0.0282   1.0000   1.0000
   0.750   0.2068   0.00968   0.00224  -0.0282   1.0000   1.0000
   1.000   0.2341   0.00977   0.00261  -0.0281   1.0000   1.0000
   1.250   0.3004   0.01410   0.00372  -0.0353   0.0374   1.0000
   1.500   0.3271   0.01532   0.00509  -0.0348   0.0248   1.0000
   1.750   0.3537   0.01672   0.00664  -0.0341   0.0220   1.0000
   2.000   0.3810   0.01807   0.00809  -0.0337   0.0163   1.0000
   2.250   0.4085   0.01997   0.01018  -0.0333   0.0116   1.0000
   2.500   0.4372   0.02210   0.01265  -0.0327   0.0112   1.0000
   2.750   0.4656   0.02466   0.01598  -0.0321   0.0119   1.0000
   3.000   0.4935   0.02744   0.01925  -0.0315   0.0121   1.0000
   3.250   0.5204   0.03059   0.02288  -0.0310   0.0123   1.0000
   3.500   0.5458   0.03423   0.02699  -0.0307   0.0127   1.0000
   4.000   0.6012   0.04032   0.03397  -0.0294   0.0159   1.0000
   4.250   0.6277   0.04503   0.03914  -0.0292   0.0194   1.0000
   4.500   0.6452   0.05181   0.04582  -0.0289   0.0392   1.0000
   5.000   0.6957   0.05925   0.05428  -0.0315   0.0335   1.0000
   5.250   0.7149   0.06390   0.05915  -0.0333   0.0322   1.0000
   5.500   0.7321   0.06864   0.06406  -0.0355   0.0310   1.0000
   5.750   0.7471   0.07344   0.06899  -0.0379   0.0299   1.0000
   6.000   0.7600   0.07825   0.07390  -0.0404   0.0290   1.0000
   6.250   0.7706   0.08305   0.07876  -0.0427   0.0282   1.0000
   6.500   0.7789   0.08783   0.08359  -0.0446   0.0275   1.0000
   6.750   0.7844   0.09278   0.08855  -0.0454   0.0269   1.0000
   7.000   0.7833   0.09957   0.09530  -0.0448   0.0260   1.0000
   7.250   0.7889   0.10503   0.10074  -0.0478   0.0259   1.0000
   7.750   0.7996   0.11451   0.11041  -0.0552   0.0258   1.0000
   8.000   0.8024   0.11899   0.11487  -0.0590   0.0258   1.0000
   8.250   0.8053   0.12335   0.11920  -0.0621   0.0258   1.0000
   8.500   0.8079   0.12761   0.12343  -0.0651   0.0257   1.0000
   8.750   0.8107   0.13179   0.12759  -0.0678   0.0257   1.0000
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