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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 100,000
Max Cl/Cd: 21.77 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20403-il-100000-n5.txt
Download as CSV file: xf-sc20403-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0403 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6766   0.10928   0.10439   0.0212   1.0000   0.0275
  -8.500  -0.6723   0.10512   0.10025   0.0206   1.0000   0.0281
  -8.250  -0.6685   0.10115   0.09631   0.0193   1.0000   0.0287
  -8.000  -0.6649   0.09723   0.09242   0.0175   1.0000   0.0292
  -7.750  -0.6612   0.09323   0.08846   0.0150   1.0000   0.0297
  -7.500  -0.6544   0.08881   0.08407   0.0111   1.0000   0.0303
  -7.250  -0.6452   0.08403   0.07930   0.0061   1.0000   0.0310
  -7.000  -0.6338   0.07905   0.07429   0.0008   1.0000   0.0317
  -6.750  -0.6202   0.07399   0.06918  -0.0044   1.0000   0.0325
  -6.500  -0.6043   0.06891   0.06401  -0.0093   1.0000   0.0335
  -6.250  -0.5859   0.06383   0.05880  -0.0138   1.0000   0.0345
  -6.000  -0.5512   0.06042   0.05472  -0.0213   1.0000   0.0389
  -5.750  -0.5292   0.05612   0.05013  -0.0234   1.0000   0.0390
  -5.500  -0.5169   0.04827   0.04251  -0.0235   1.0000   0.0209
  -5.250  -0.4895   0.04311   0.03699  -0.0260   1.0000   0.0175
  -4.750  -0.4279   0.03600   0.02894  -0.0276   1.0000   0.0133
  -4.500  -0.4000   0.03170   0.02419  -0.0290   1.0000   0.0128
  -4.250  -0.3704   0.02815   0.02014  -0.0299   1.0000   0.0125
  -4.000  -0.3404   0.02509   0.01656  -0.0304   1.0000   0.0123
  -3.750  -0.3106   0.02244   0.01342  -0.0305   1.0000   0.0122
  -3.500  -0.2816   0.02007   0.01033  -0.0302   1.0000   0.0116
  -3.250  -0.2535   0.01849   0.00849  -0.0298   1.0000   0.0141
  -3.000  -0.2264   0.01682   0.00672  -0.0299   1.0000   0.0214
  -2.750  -0.1985   0.01536   0.00512  -0.0296   1.0000   0.0241
  -2.500  -0.1696   0.01407   0.00365  -0.0297   1.0000   0.0314
  -2.250  -0.1451   0.01058   0.00277  -0.0301   1.0000   0.6326
  -2.000  -0.1442   0.00993   0.00279  -0.0219   1.0000   0.8663
  -1.750  -0.1241   0.00939   0.00223  -0.0188   1.0000   1.0000
  -1.500  -0.0953   0.00934   0.00191  -0.0193   1.0000   1.0000
  -1.250  -0.0668   0.00931   0.00169  -0.0198   1.0000   1.0000
  -1.000  -0.0384   0.00929   0.00147  -0.0201   1.0000   1.0000
  -0.750  -0.0104   0.00928   0.00135  -0.0204   1.0000   1.0000
  -0.500   0.0175   0.00929   0.00129  -0.0206   1.0000   1.0000
  -0.250   0.0451   0.00930   0.00128  -0.0208   1.0000   1.0000
   0.000   0.0727   0.00932   0.00131  -0.0209   1.0000   1.0000
   0.250   0.1001   0.00935   0.00141  -0.0210   1.0000   1.0000
   0.500   0.1274   0.00940   0.00155  -0.0210   1.0000   1.0000
   0.750   0.1546   0.00945   0.00180  -0.0210   1.0000   1.0000
   1.000   0.1818   0.00951   0.00204  -0.0209   1.0000   1.0000
   1.250   0.2088   0.00959   0.00238  -0.0208   1.0000   1.0000
   1.500   0.2682   0.01347   0.00321  -0.0267   0.0550   1.0000
   1.750   0.2950   0.01482   0.00453  -0.0263   0.0258   1.0000
   2.000   0.3219   0.01606   0.00597  -0.0256   0.0224   1.0000
   2.250   0.3491   0.01749   0.00752  -0.0251   0.0183   1.0000
   2.500   0.3761   0.01923   0.00939  -0.0249   0.0120   1.0000
   2.750   0.4047   0.02120   0.01169  -0.0243   0.0112   1.0000
   3.000   0.4332   0.02368   0.01492  -0.0237   0.0118   1.0000
   3.250   0.4615   0.02640   0.01814  -0.0232   0.0120   1.0000
   3.500   0.4890   0.02947   0.02172  -0.0227   0.0122   1.0000
   3.750   0.5153   0.03296   0.02568  -0.0224   0.0126   1.0000
   4.000   0.5392   0.03726   0.03040  -0.0225   0.0131   1.0000
   4.500   0.5974   0.04396   0.03803  -0.0216   0.0176   1.0000
   4.750   0.6217   0.04878   0.04321  -0.0222   0.0210   1.0000
   5.250   0.6562   0.06049   0.05510  -0.0232   0.0384   1.0000
   5.500   0.6880   0.06354   0.05876  -0.0269   0.0332   1.0000
   5.750   0.7064   0.06839   0.06378  -0.0295   0.0322   1.0000
   6.000   0.7226   0.07329   0.06882  -0.0325   0.0312   1.0000
   6.250   0.7368   0.07820   0.07383  -0.0357   0.0303   1.0000
   6.500   0.7488   0.08309   0.07879  -0.0391   0.0295   1.0000
   6.750   0.7588   0.08793   0.08368  -0.0424   0.0288   1.0000
   7.000   0.7670   0.09270   0.08847  -0.0455   0.0282   1.0000
   7.250   0.7735   0.09742   0.09320  -0.0480   0.0276   1.0000
   7.500   0.7784   0.10216   0.09794  -0.0495   0.0270   1.0000
   7.750   0.7800   0.10771   0.10347  -0.0484   0.0263   1.0000
   8.000   0.7797   0.11418   0.11002  -0.0500   0.0259   1.0000
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