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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 200,000
Max Cl/Cd: 28.86 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20403-il-200000-n5.txt
Download as CSV file: xf-sc20403-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6643   0.10961   0.10607   0.0218   1.0000   0.0135
  -8.500  -0.6600   0.10560   0.10209   0.0196   1.0000   0.0135
  -8.250  -0.6557   0.10156   0.09807   0.0172   1.0000   0.0135
  -8.000  -0.6513   0.09744   0.09398   0.0143   1.0000   0.0136
  -7.750  -0.6438   0.09286   0.08942   0.0099   1.0000   0.0136
  -7.500  -0.6330   0.08776   0.08431   0.0041   1.0000   0.0136
  -7.250  -0.6206   0.08261   0.07912  -0.0012   1.0000   0.0136
  -7.000  -0.6071   0.07755   0.07401  -0.0057   1.0000   0.0136
  -6.750  -0.5923   0.07257   0.06894  -0.0097   1.0000   0.0136
  -6.500  -0.5809   0.06577   0.06207  -0.0140   1.0000   0.0139
  -6.250  -0.5688   0.05907   0.05524  -0.0179   1.0000   0.0145
  -6.000  -0.5521   0.05391   0.04994  -0.0207   1.0000   0.0150
  -5.750  -0.5320   0.04931   0.04517  -0.0232   1.0000   0.0155
  -5.500  -0.5087   0.04485   0.04048  -0.0254   1.0000   0.0159
  -5.250  -0.4820   0.04037   0.03570  -0.0273   1.0000   0.0158
  -4.750  -0.4266   0.03240   0.02709  -0.0298   1.0000   0.0105
  -4.500  -0.3964   0.02834   0.02260  -0.0309   1.0000   0.0092
  -4.250  -0.3652   0.02463   0.01841  -0.0315   1.0000   0.0082
  -4.000  -0.3336   0.02127   0.01454  -0.0317   1.0000   0.0074
  -3.750  -0.3029   0.01849   0.01128  -0.0316   1.0000   0.0068
  -3.500  -0.2733   0.01657   0.00874  -0.0312   1.0000   0.0058
  -3.250  -0.2448   0.01478   0.00670  -0.0310   1.0000   0.0058
  -3.000  -0.2162   0.01312   0.00486  -0.0311   1.0000   0.0061
  -2.750  -0.1870   0.01185   0.00344  -0.0314   1.0000   0.0069
  -2.500  -0.1584   0.01119   0.00268  -0.0316   1.0000   0.0108
  -2.250  -0.1292   0.01049   0.00191  -0.0319   1.0000   0.0276
  -2.000  -0.1006   0.00763   0.00163  -0.0337   1.0000   0.6812
  -1.750  -0.0823   0.00729   0.00165  -0.0308   1.0000   0.8057
  -1.500  -0.0674   0.00708   0.00159  -0.0271   1.0000   0.8789
  -1.250  -0.0504   0.00687   0.00141  -0.0242   1.0000   0.9223
  -1.000  -0.0263   0.00670   0.00118  -0.0231   1.0000   0.9635
  -0.750   0.0010   0.00662   0.00106  -0.0231   1.0000   1.0000
  -0.500   0.0296   0.00663   0.00102  -0.0235   1.0000   1.0000
  -0.250   0.0579   0.00665   0.00102  -0.0238   1.0000   1.0000
   0.000   0.0861   0.00667   0.00106  -0.0240   1.0000   1.0000
   0.250   0.1140   0.00670   0.00114  -0.0242   1.0000   1.0000
   0.500   0.1418   0.00674   0.00125  -0.0243   1.0000   1.0000
   0.750   0.1695   0.00678   0.00144  -0.0244   1.0000   1.0000
   1.000   0.1971   0.00683   0.00165  -0.0244   1.0000   1.0000
   1.250   0.2495   0.01047   0.00195  -0.0298   0.0366   1.0000
   1.500   0.2774   0.01126   0.00275  -0.0297   0.0111   1.0000
   1.750   0.3053   0.01187   0.00343  -0.0297   0.0068   1.0000
   2.000   0.3325   0.01308   0.00478  -0.0294   0.0059   1.0000
   2.250   0.3596   0.01469   0.00655  -0.0289   0.0056   1.0000
   2.500   0.3874   0.01649   0.00859  -0.0284   0.0056   1.0000
   2.750   0.4163   0.01821   0.01086  -0.0278   0.0064   1.0000
   3.000   0.4452   0.02073   0.01384  -0.0270   0.0069   1.0000
   3.250   0.4742   0.02383   0.01745  -0.0261   0.0076   1.0000
   3.500   0.5024   0.02724   0.02133  -0.0253   0.0085   1.0000
   3.750   0.5296   0.03092   0.02544  -0.0247   0.0096   1.0000
   4.000   0.5549   0.03497   0.02988  -0.0245   0.0111   1.0000
   4.500   0.6052   0.04248   0.03800  -0.0243   0.0155   1.0000
   4.750   0.6281   0.04667   0.04246  -0.0248   0.0153   1.0000
   5.000   0.6486   0.05099   0.04699  -0.0255   0.0149   1.0000
   5.250   0.6660   0.05573   0.05190  -0.0266   0.0144   1.0000
   5.500   0.6795   0.06189   0.05824  -0.0284   0.0138   1.0000
   5.750   0.6900   0.06935   0.06582  -0.0309   0.0133   1.0000
   6.000   0.7062   0.07425   0.07085  -0.0330   0.0133   1.0000
   6.250   0.7210   0.07921   0.07592  -0.0355   0.0133   1.0000
   6.500   0.7345   0.08421   0.08102  -0.0385   0.0133   1.0000
   6.750   0.7465   0.08924   0.08612  -0.0419   0.0133   1.0000
   7.000   0.7570   0.09425   0.09117  -0.0457   0.0133   1.0000
   7.250   0.7659   0.09923   0.09618  -0.0498   0.0132   1.0000
   7.500   0.7730   0.10408   0.10104  -0.0541   0.0132   1.0000
   7.750   0.7762   0.10856   0.10550  -0.0578   0.0132   1.0000
   8.000   0.7791   0.11290   0.10982  -0.0608   0.0132   1.0000
   8.250   0.7822   0.11716   0.11406  -0.0634   0.0132   1.0000
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