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NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il)
Reynolds number: 1,000,000
Max Cl/Cd: 59.81 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20406-il-1000000.txt
Download as CSV file: xf-sc20406-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0406 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.6124   0.01742   0.01305  -0.0320   1.0000   0.0090
  -6.500  -0.5852   0.01581   0.01119  -0.0322   1.0000   0.0093
  -6.250  -0.5576   0.01436   0.00953  -0.0325   1.0000   0.0094
  -6.000  -0.5299   0.01314   0.00816  -0.0327   1.0000   0.0095
  -5.750  -0.5019   0.01225   0.00716  -0.0329   1.0000   0.0097
  -5.500  -0.4737   0.01114   0.00592  -0.0332   1.0000   0.0100
  -5.250  -0.4448   0.00996   0.00457  -0.0337   1.0000   0.0103
  -5.000  -0.4154   0.00910   0.00359  -0.0342   1.0000   0.0109
  -4.750  -0.3863   0.00860   0.00304  -0.0346   1.0000   0.0124
  -4.500  -0.3575   0.00827   0.00268  -0.0349   1.0000   0.0140
  -4.250  -0.3286   0.00792   0.00229  -0.0351   1.0000   0.0173
  -4.000  -0.2997   0.00759   0.00203  -0.0355   1.0000   0.0318
  -3.750  -0.2713   0.00738   0.00186  -0.0357   1.0000   0.0420
  -3.500  -0.2430   0.00718   0.00170  -0.0359   1.0000   0.0528
  -3.250  -0.2147   0.00696   0.00156  -0.0361   1.0000   0.0713
  -3.000  -0.1862   0.00667   0.00140  -0.0365   1.0000   0.1058
  -2.750  -0.1573   0.00618   0.00124  -0.0371   1.0000   0.1970
  -2.500  -0.1272   0.00531   0.00105  -0.0383   1.0000   0.3903
  -2.250  -0.0984   0.00480   0.00098  -0.0390   1.0000   0.5226
  -2.000  -0.0707   0.00461   0.00096  -0.0390   1.0000   0.5827
  -1.750  -0.0435   0.00449   0.00096  -0.0390   1.0000   0.6216
  -1.500  -0.0163   0.00440   0.00099  -0.0388   1.0000   0.6578
  -1.250   0.0108   0.00435   0.00104  -0.0387   1.0000   0.6866
  -1.000   0.0380   0.00432   0.00110  -0.0386   1.0000   0.7117
  -0.750   0.0810   0.00419   0.00103  -0.0419   0.9929   0.7321
  -0.500   0.1212   0.00412   0.00103  -0.0446   0.9734   0.7556
  -0.250   0.1517   0.00413   0.00108  -0.0449   0.9492   0.7739
   0.000   0.1764   0.00420   0.00112  -0.0438   0.9130   0.7864
   0.250   0.2007   0.00436   0.00114  -0.0426   0.8623   0.7970
   0.500   0.2263   0.00458   0.00115  -0.0419   0.7984   0.8075
   0.750   0.2521   0.00496   0.00119  -0.0413   0.6941   0.8170
   1.000   0.2783   0.00558   0.00129  -0.0412   0.5377   0.8258
   1.500   0.3313   0.00716   0.00164  -0.0415   0.1822   0.8435
   1.750   0.3586   0.00760   0.00181  -0.0415   0.1022   0.8526
   2.000   0.3862   0.00789   0.00196  -0.0416   0.0649   0.8623
   2.250   0.4136   0.00807   0.00214  -0.0414   0.0501   0.8717
   2.500   0.4410   0.00824   0.00231  -0.0413   0.0400   0.8816
   2.750   0.4683   0.00843   0.00249  -0.0411   0.0294   0.8921
   3.000   0.4951   0.00874   0.00275  -0.0409   0.0161   0.9034
   3.250   0.5213   0.00912   0.00324  -0.0403   0.0131   0.9154
   3.500   0.5469   0.00939   0.00359  -0.0397   0.0125   0.9288
   3.750   0.5707   0.00966   0.00396  -0.0387   0.0118   0.9462
   4.000   0.5933   0.00992   0.00431  -0.0374   0.0110   1.0000
   4.250   0.6217   0.01043   0.00486  -0.0375   0.0101   1.0000
   4.500   0.6492   0.01126   0.00580  -0.0375   0.0094   1.0000
   4.750   0.6759   0.01242   0.00708  -0.0372   0.0091   1.0000
   5.000   0.7024   0.01371   0.00853  -0.0370   0.0091   1.0000
   5.250   0.7280   0.01561   0.01065  -0.0365   0.0089   1.0000
   5.500   0.7531   0.01782   0.01315  -0.0361   0.0088   1.0000
   5.750   0.7781   0.01975   0.01534  -0.0356   0.0088   1.0000
   6.000   0.8022   0.02192   0.01782  -0.0351   0.0089   1.0000
   6.250   0.8244   0.02478   0.02104  -0.0343   0.0090   1.0000
   6.500   0.8232   0.04250   0.04010  -0.0303   0.0101   1.0000
   6.750   0.8385   0.04663   0.04445  -0.0302   0.0097   1.0000
   7.000   0.8519   0.05062   0.04861  -0.0303   0.0094   1.0000
   7.250   0.8622   0.05523   0.05340  -0.0307   0.0092   1.0000
   7.500   0.8661   0.06154   0.05989  -0.0318   0.0089   1.0000
  14.500   0.6585   0.17658   0.17524  -0.0703   0.0060   1.0000
  14.750   0.6613   0.17925   0.17791  -0.0714   0.0059   1.0000
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