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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 500,000
Max Cl/Cd: 35.25 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20503-il-500000-n5.txt
Download as CSV file: xf-sc20503-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6410   0.10227   0.09999   0.0177   1.0000   0.0052
  -8.500  -0.6368   0.09832   0.09606   0.0156   1.0000   0.0052
  -8.250  -0.6327   0.09437   0.09213   0.0133   1.0000   0.0052
  -8.000  -0.6280   0.09030   0.08808   0.0104   1.0000   0.0052
  -7.750  -0.6184   0.08557   0.08336   0.0053   1.0000   0.0052
  -7.500  -0.6056   0.08032   0.07811  -0.0012   1.0000   0.0052
  -7.250  -0.5908   0.07491   0.07266  -0.0075   1.0000   0.0052
  -7.000  -0.5746   0.06961   0.06731  -0.0128   1.0000   0.0052
  -6.750  -0.5569   0.06442   0.06204  -0.0174   1.0000   0.0052
  -6.500  -0.5378   0.05935   0.05686  -0.0213   1.0000   0.0052
  -6.250  -0.5188   0.05294   0.05033  -0.0255   1.0000   0.0053
  -6.000  -0.4983   0.04617   0.04334  -0.0295   1.0000   0.0056
  -5.750  -0.4747   0.04067   0.03761  -0.0323   1.0000   0.0058
  -5.500  -0.4488   0.03598   0.03266  -0.0345   1.0000   0.0059
  -5.250  -0.4210   0.03180   0.02819  -0.0362   1.0000   0.0061
  -5.000  -0.3914   0.02796   0.02404  -0.0374   1.0000   0.0061
  -4.500  -0.3328   0.02292   0.01849  -0.0385   1.0000   0.0049
  -4.250  -0.3003   0.01892   0.01402  -0.0397   1.0000   0.0044
  -4.000  -0.2686   0.01598   0.01064  -0.0403   1.0000   0.0041
  -3.750  -0.2380   0.01359   0.00776  -0.0404   1.0000   0.0037
  -3.500  -0.2081   0.01162   0.00552  -0.0404   1.0000   0.0035
  -3.250  -0.1782   0.01008   0.00379  -0.0407   1.0000   0.0033
  -3.000  -0.1479   0.00897   0.00253  -0.0412   1.0000   0.0034
  -2.750  -0.1185   0.00831   0.00171  -0.0415   1.0000   0.0037
  -2.500  -0.0904   0.00798   0.00126  -0.0415   1.0000   0.0045
  -2.250  -0.0631   0.00777   0.00105  -0.0414   1.0000   0.0105
  -2.000  -0.0309   0.00646   0.00084  -0.0435   1.0000   0.3233
  -1.750   0.0000   0.00530   0.00086  -0.0450   1.0000   0.6723
  -1.500   0.0264   0.00512   0.00090  -0.0446   1.0000   0.7486
  -1.250   0.0526   0.00504   0.00091  -0.0442   1.0000   0.7788
  -1.000   0.0786   0.00498   0.00094  -0.0438   1.0000   0.8043
  -0.750   0.1048   0.00495   0.00097  -0.0434   1.0000   0.8240
  -0.500   0.1308   0.00492   0.00102  -0.0429   1.0000   0.8396
  -0.250   0.1569   0.00490   0.00109  -0.0425   1.0000   0.8542
   0.250   0.2300   0.00714   0.00115  -0.0464   0.3111   0.8763
   0.500   0.2537   0.00839   0.00136  -0.0462   0.0116   0.8892
   0.750   0.2794   0.00855   0.00154  -0.0456   0.0044   0.9025
   1.000   0.3044   0.00877   0.00191  -0.0448   0.0036   0.9190
   1.500   0.3543   0.01005   0.00355  -0.0428   0.0032   1.0000
   1.750   0.3815   0.01142   0.00507  -0.0423   0.0033   1.0000
   2.000   0.4092   0.01320   0.00706  -0.0417   0.0035   1.0000
   2.250   0.4376   0.01538   0.00953  -0.0410   0.0038   1.0000
   2.500   0.4657   0.01785   0.01252  -0.0403   0.0041   1.0000
   2.750   0.4932   0.02089   0.01596  -0.0395   0.0045   1.0000
   3.000   0.5177   0.02530   0.02082  -0.0388   0.0052   1.0000
   3.250   0.5464   0.02601   0.02165  -0.0382   0.0058   1.0000
   3.500   0.5731   0.02916   0.02512  -0.0373   0.0060   1.0000
   3.750   0.5980   0.03270   0.02896  -0.0367   0.0060   1.0000
   4.000   0.6214   0.03653   0.03307  -0.0364   0.0058   1.0000
   4.250   0.6432   0.04085   0.03765  -0.0363   0.0056   1.0000
   4.500   0.6630   0.04602   0.04308  -0.0365   0.0054   1.0000
   4.750   0.6796   0.05286   0.05019  -0.0374   0.0052   1.0000
   5.000   0.6976   0.05849   0.05597  -0.0385   0.0051   1.0000
   5.250   0.7160   0.06332   0.06095  -0.0398   0.0051   1.0000
   5.500   0.7332   0.06827   0.06603  -0.0416   0.0051   1.0000
   5.750   0.7490   0.07335   0.07121  -0.0439   0.0051   1.0000
   6.000   0.7632   0.07849   0.07643  -0.0467   0.0051   1.0000
   6.250   0.7759   0.08368   0.08170  -0.0500   0.0051   1.0000
   6.500   0.7868   0.08888   0.08694  -0.0537   0.0051   1.0000
   6.750   0.7959   0.09404   0.09214  -0.0578   0.0051   1.0000
   7.000   0.8032   0.09913   0.09724  -0.0623   0.0051   1.0000
   7.250   0.8061   0.10385   0.10196  -0.0664   0.0051   1.0000
   7.500   0.8073   0.10829   0.10638  -0.0697   0.0051   1.0000
   7.750   0.8090   0.11265   0.11073  -0.0722   0.0051   1.0000
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