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NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il)
Reynolds number: 50,000
Max Cl/Cd: 14.19 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20402-il-50000.txt
Download as CSV file: xf-sc20402-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0402 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7209   0.12319   0.11672   0.0305   1.0000   0.1320
  -8.750  -0.7055   0.11683   0.11034   0.0332   1.0000   0.1425
  -8.500  -0.7142   0.11537   0.10900   0.0279   1.0000   0.1450
  -8.250  -0.7014   0.10977   0.10339   0.0300   1.0000   0.1563
  -8.000  -0.6949   0.10539   0.09905   0.0299   1.0000   0.1644
  -7.750  -0.6991   0.10319   0.09695   0.0218   1.0000   0.1712
  -7.500  -0.6910   0.09872   0.09250   0.0216   1.0000   0.1839
  -7.250  -0.6842   0.09465   0.08845   0.0190   1.0000   0.1971
  -7.000  -0.6751   0.08998   0.08382   0.0200   1.0000   0.2125
  -6.750  -0.6657   0.08596   0.07979   0.0208   1.0000   0.2336
  -6.500  -0.5724   0.07025   0.06400   0.0219   1.0000   0.2962
  -6.250  -0.6507   0.07822   0.07157   0.0174   1.0000   0.2895
  -6.000  -0.6402   0.07440   0.06781   0.0238   1.0000   0.3232
  -5.750  -0.6338   0.07119   0.06466   0.0272   1.0000   0.3700
  -5.500  -0.6255   0.06819   0.06172   0.0349   1.0000   0.4246
  -4.750  -0.4442   0.04900   0.04212   0.0572   1.0000   0.9106
  -4.500  -0.4718   0.04889   0.04217   0.0620   1.0000   0.8664
  -4.250  -0.3936   0.03751   0.02778  -0.0298   1.0000   0.1313
  -4.000  -0.3580   0.03359   0.02330  -0.0305   1.0000   0.1004
  -3.750  -0.3209   0.03103   0.01977  -0.0306   1.0000   0.0806
  -3.500  -0.2913   0.02801   0.01648  -0.0306   1.0000   0.0755
  -3.250  -0.2611   0.02571   0.01376  -0.0303   1.0000   0.0750
  -3.000  -0.2318   0.02383   0.01149  -0.0297   1.0000   0.0777
  -2.750  -0.2040   0.02220   0.00958  -0.0285   1.0000   0.0802
  -2.500  -0.1790   0.02038   0.00772  -0.0269   1.0000   0.0825
  -2.250  -0.1521   0.01898   0.00619  -0.0259   1.0000   0.0853
  -1.750  -0.1123   0.01291   0.00332  -0.0194   1.0000   1.0000
  -1.500  -0.0835   0.01288   0.00232  -0.0187   1.0000   1.0000
  -1.250  -0.0559   0.01284   0.00184  -0.0186   1.0000   1.0000
  -1.000  -0.0286   0.01282   0.00152  -0.0186   1.0000   1.0000
  -0.750  -0.0015   0.01280   0.00132  -0.0186   1.0000   1.0000
  -0.500   0.0256   0.01280   0.00123  -0.0185   1.0000   1.0000
  -0.250   0.0525   0.01282   0.00122  -0.0184   1.0000   1.0000
   0.000   0.0793   0.01284   0.00132  -0.0183   1.0000   1.0000
   0.250   0.1061   0.01288   0.00152  -0.0182   1.0000   1.0000
   0.500   0.1329   0.01293   0.00182  -0.0180   1.0000   1.0000
   0.750   0.1598   0.01299   0.00228  -0.0177   1.0000   1.0000
   1.000   0.2114   0.01512   0.00362  -0.0198   0.3233   1.0000
   1.250   0.2379   0.01837   0.00553  -0.0193   0.0885   1.0000
   1.500   0.2660   0.01973   0.00705  -0.0186   0.0827   1.0000
   1.750   0.2954   0.02145   0.00889  -0.0178   0.0805   1.0000
   2.000   0.3256   0.02326   0.01090  -0.0171   0.0780   1.0000
   2.250   0.3557   0.02507   0.01307  -0.0164   0.0746   1.0000
   2.500   0.3857   0.02723   0.01562  -0.0159   0.0737   1.0000
   2.750   0.4156   0.02992   0.01868  -0.0154   0.0777   1.0000
   3.000   0.4474   0.03265   0.02201  -0.0147   0.0906   1.0000
   3.250   0.4820   0.03564   0.02578  -0.0142   0.1155   1.0000
   3.500   0.5223   0.03947   0.03052  -0.0147   0.1694   1.0000
   3.750   0.6271   0.05112   0.04522  -0.1006   0.7892   1.0000
   4.000   0.5857   0.05208   0.04599  -0.0983   0.8578   1.0000
   4.250   0.6393   0.05816   0.05215  -0.1034   0.7989   1.0000
   5.250   0.7425   0.07359   0.06749  -0.0511   0.3294   1.0000
   5.500   0.7505   0.07764   0.07147  -0.0468   0.2893   1.0000
   5.750   0.6677   0.07062   0.06492  -0.0474   0.2961   1.0000
   6.000   0.6725   0.07513   0.06939  -0.0465   0.2688   1.0000
   6.250   0.7748   0.09071   0.08509  -0.0468   0.2098   1.0000
   6.500   0.7797   0.09456   0.08896  -0.0518   0.1939   1.0000
   6.750   0.7859   0.09890   0.09327  -0.0538   0.1808   1.0000
   7.000   0.7932   0.10354   0.09790  -0.0544   0.1695   1.0000
   7.250   0.8023   0.10867   0.10301  -0.0530   0.1578   1.0000
   7.500   0.7965   0.11130   0.10557  -0.0611   0.1529   1.0000
   7.750   0.8063   0.11664   0.11090  -0.0597   0.1442   1.0000
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