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NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il)
Reynolds number: 200,000
Max Cl/Cd: 52.34 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20503-il-200000.txt
Download as CSV file: xf-sc20503-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6775   0.12966   0.12604   0.0311   1.0000   0.0186
 -10.250  -0.6733   0.12589   0.12227   0.0294   1.0000   0.0191
 -10.000  -0.6692   0.12213   0.11853   0.0277   1.0000   0.0196
  -9.750  -0.6649   0.11842   0.11484   0.0258   1.0000   0.0201
  -9.500  -0.6606   0.11478   0.11122   0.0236   1.0000   0.0205
  -9.250  -0.6563   0.11123   0.10769   0.0211   1.0000   0.0210
  -9.000  -0.6520   0.10771   0.10420   0.0183   1.0000   0.0213
  -8.750  -0.6475   0.10417   0.10069   0.0152   1.0000   0.0215
  -8.500  -0.6429   0.10054   0.09709   0.0121   1.0000   0.0217
  -8.250  -0.6379   0.09671   0.09329   0.0083   1.0000   0.0218
  -8.000  -0.6276   0.09219   0.08878   0.0026   1.0000   0.0220
  -7.750  -0.6148   0.08719   0.08376  -0.0040   1.0000   0.0220
  -7.500  -0.6009   0.08228   0.07880  -0.0094   1.0000   0.0221
  -7.250  -0.5860   0.07748   0.07384  -0.0140   1.0000   0.0222
  -7.000  -0.5701   0.07277   0.06901  -0.0180   1.0000   0.0222
  -6.750  -0.5647   0.06452   0.06075  -0.0217   1.0000   0.0231
  -6.500  -0.5552   0.05981   0.05605  -0.0226   1.0000   0.0243
  -6.250  -0.5386   0.05558   0.05174  -0.0249   1.0000   0.0257
  -6.000  -0.5172   0.05119   0.04719  -0.0278   1.0000   0.0275
  -5.750  -0.4923   0.04677   0.04254  -0.0307   1.0000   0.0298
  -5.500  -0.4597   0.04331   0.03867  -0.0332   1.0000   0.0337
  -5.250  -0.4298   0.03855   0.03336  -0.0359   1.0000   0.0359
  -5.000  -0.4085   0.03424   0.02909  -0.0374   1.0000   0.0392
  -3.750  -0.2516   0.01876   0.01133  -0.0400   1.0000   0.0271
  -3.500  -0.2211   0.01682   0.00902  -0.0391   1.0000   0.0205
  -3.250  -0.1919   0.01474   0.00668  -0.0388   1.0000   0.0198
  -3.000  -0.1633   0.01311   0.00493  -0.0387   1.0000   0.0242
  -2.750  -0.1346   0.01195   0.00379  -0.0389   1.0000   0.0325
  -2.500  -0.1036   0.01070   0.00247  -0.0395   1.0000   0.0485
  -2.250  -0.0807   0.00746   0.00207  -0.0388   1.0000   0.8073
  -2.000  -0.0788   0.00712   0.00197  -0.0314   1.0000   0.9102
  -1.750  -0.0642   0.00673   0.00159  -0.0278   1.0000   1.0000
  -1.500  -0.0334   0.00672   0.00142  -0.0288   1.0000   1.0000
  -1.250  -0.0032   0.00672   0.00128  -0.0296   1.0000   1.0000
  -1.000   0.0265   0.00673   0.00121  -0.0303   1.0000   1.0000
  -0.750   0.0556   0.00674   0.00118  -0.0308   1.0000   1.0000
  -0.500   0.0844   0.00677   0.00119  -0.0313   1.0000   1.0000
  -0.250   0.1129   0.00680   0.00124  -0.0316   1.0000   1.0000
   0.000   0.1411   0.00684   0.00133  -0.0318   1.0000   1.0000
   0.250   0.1692   0.00689   0.00146  -0.0320   1.0000   1.0000
   0.500   0.1971   0.00695   0.00166  -0.0321   1.0000   1.0000
   0.750   0.2249   0.00701   0.00190  -0.0322   1.0000   1.0000
   1.000   0.2844   0.01105   0.00280  -0.0385   0.0441   1.0000
   1.250   0.3115   0.01235   0.00414  -0.0381   0.0319   1.0000
   1.500   0.3390   0.01363   0.00545  -0.0376   0.0278   1.0000
   1.750   0.3663   0.01525   0.00712  -0.0373   0.0194   1.0000
   2.000   0.3950   0.01735   0.00946  -0.0366   0.0198   1.0000
   2.250   0.4109   0.00785   0.00069  -0.0325   0.0263   1.0000
   2.500   0.4640   0.02328   0.01654  -0.0327   0.0796   1.0000
   2.750   0.4901   0.02556   0.01903  -0.0325   0.0641   1.0000
   3.000   0.5168   0.02811   0.02213  -0.0321   0.0531   1.0000
   3.250   0.5388   0.03256   0.02650  -0.0326   0.0478   1.0000
   3.500   0.5680   0.03388   0.02856  -0.0316   0.0388   1.0000
   3.750   0.5884   0.03774   0.03245  -0.0319   0.0354   1.0000
   4.000   0.6076   0.04386   0.03890  -0.0322   0.0337   1.0000
   4.250   0.6409   0.04508   0.04072  -0.0315   0.0294   1.0000
   4.500   0.6641   0.04905   0.04495  -0.0320   0.0270   1.0000
   4.750   0.6847   0.05314   0.04924  -0.0328   0.0251   1.0000
   5.000   0.7016   0.05729   0.05353  -0.0336   0.0236   1.0000
   5.250   0.7125   0.06225   0.05851  -0.0341   0.0223   1.0000
   5.500   0.7171   0.07103   0.06736  -0.0360   0.0214   1.0000
   5.750   0.7332   0.07557   0.07208  -0.0376   0.0213   1.0000
   6.000   0.7485   0.08018   0.07692  -0.0398   0.0213   1.0000
   6.250   0.7629   0.08482   0.08168  -0.0426   0.0211   1.0000
   6.500   0.7764   0.08949   0.08644  -0.0461   0.0210   1.0000
   6.750   0.7885   0.09427   0.09130  -0.0507   0.0208   1.0000
   7.000   0.7987   0.09907   0.09614  -0.0561   0.0206   1.0000
   7.250   0.8045   0.10369   0.10076  -0.0615   0.0204   1.0000
   7.500   0.8065   0.10798   0.10503  -0.0658   0.0202   1.0000
   7.750   0.8087   0.11214   0.10916  -0.0692   0.0199   1.0000
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