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NACA 16009 (naca16009-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 16009 (naca16009-il)
Reynolds number: 50,000
Max Cl/Cd: 19.81 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16009-il-50000-n5.txt
Download as CSV file: xf-naca16009-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16009                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6084   0.10051   0.09335  -0.0280   1.0000   0.0393
  -9.750  -0.6138   0.09535   0.08823  -0.0308   1.0000   0.0388
  -9.500  -0.6222   0.09040   0.08331  -0.0332   1.0000   0.0382
  -9.250  -0.6338   0.08597   0.07890  -0.0343   1.0000   0.0376
  -9.000  -0.6479   0.08213   0.07506  -0.0337   1.0000   0.0370
  -8.750  -0.6636   0.07875   0.07167  -0.0317   1.0000   0.0366
  -8.500  -0.6764   0.07525   0.06811  -0.0296   1.0000   0.0363
  -8.250  -0.6872   0.07181   0.06457  -0.0271   1.0000   0.0362
  -8.000  -0.6960   0.06843   0.06105  -0.0243   1.0000   0.0364
  -7.750  -0.7025   0.06508   0.05751  -0.0213   1.0000   0.0367
  -7.500  -0.7068   0.06176   0.05397  -0.0181   1.0000   0.0372
  -7.250  -0.7089   0.05846   0.05039  -0.0148   1.0000   0.0377
  -7.000  -0.7086   0.05518   0.04679  -0.0114   1.0000   0.0381
  -6.750  -0.7058   0.05192   0.04316  -0.0080   1.0000   0.0382
  -6.500  -0.7003   0.04866   0.03951  -0.0047   1.0000   0.0381
  -6.250  -0.6919   0.04549   0.03591  -0.0015   1.0000   0.0380
  -6.000  -0.6806   0.04242   0.03238   0.0014   1.0000   0.0381
  -5.750  -0.6658   0.03949   0.02895   0.0041   1.0000   0.0384
  -5.500  -0.6474   0.03673   0.02568   0.0063   1.0000   0.0391
  -5.250  -0.6250   0.03417   0.02262   0.0080   1.0000   0.0402
  -5.000  -0.5989   0.03190   0.01987   0.0091   1.0000   0.0417
  -4.750  -0.5738   0.02990   0.01780   0.0096   1.0000   0.0467
  -4.500  -0.5461   0.02848   0.01605   0.0102   1.0000   0.0552
  -4.250  -0.5176   0.02680   0.01415   0.0105   1.0000   0.0634
  -4.000  -0.4944   0.02551   0.01272   0.0116   1.0000   0.0814
  -3.750  -0.4747   0.02396   0.01131   0.0131   1.0000   0.1125
  -3.500  -0.2273   0.02342   0.01291  -0.0213   1.0000   0.9840
  -3.250  -0.1690   0.02276   0.01176  -0.0286   1.0000   0.9997
  -3.000  -0.1546   0.02244   0.01125  -0.0269   1.0000   1.0000
  -2.750  -0.1412   0.02216   0.01080  -0.0249   1.0000   1.0000
  -2.500  -0.1278   0.02191   0.01041  -0.0229   1.0000   1.0000
  -2.250  -0.1145   0.02170   0.01000  -0.0209   1.0000   1.0000
  -2.000  -0.1014   0.02151   0.00970  -0.0187   1.0000   1.0000
  -1.750  -0.0884   0.02135   0.00945  -0.0165   1.0000   1.0000
  -1.500  -0.0755   0.02122   0.00923  -0.0143   1.0000   1.0000
  -1.250  -0.0627   0.02110   0.00905  -0.0120   1.0000   1.0000
  -1.000  -0.0501   0.02102   0.00891  -0.0096   1.0000   1.0000
  -0.750  -0.0375   0.02095   0.00878  -0.0072   1.0000   1.0000
  -0.500  -0.0249   0.02090   0.00870  -0.0048   1.0000   1.0000
  -0.250  -0.0125   0.02087   0.00865  -0.0024   1.0000   1.0000
   0.000   0.0000   0.02086   0.00863   0.0000   1.0000   1.0000
   0.250   0.0125   0.02087   0.00865   0.0024   1.0000   1.0000
   0.500   0.0249   0.02090   0.00870   0.0048   1.0000   1.0000
   0.750   0.0375   0.02094   0.00878   0.0072   1.0000   1.0000
   1.000   0.0501   0.02101   0.00891   0.0096   1.0000   1.0000
   1.250   0.0627   0.02110   0.00905   0.0120   1.0000   1.0000
   1.500   0.0755   0.02121   0.00922   0.0143   1.0000   1.0000
   1.750   0.0884   0.02135   0.00944   0.0165   1.0000   1.0000
   2.000   0.1014   0.02150   0.00970   0.0187   1.0000   1.0000
   2.250   0.1145   0.02169   0.00999   0.0209   1.0000   1.0000
   2.500   0.1278   0.02190   0.01040   0.0229   1.0000   1.0000
   2.750   0.1412   0.02215   0.01079   0.0249   1.0000   1.0000
   3.000   0.1547   0.02243   0.01124   0.0269   1.0000   1.0000
   3.250   0.1689   0.02275   0.01175   0.0286   0.9997   1.0000
   3.500   0.2272   0.02341   0.01289   0.0213   0.9840   1.0000
   3.750   0.4746   0.02396   0.01131  -0.0131   0.1125   1.0000
   4.000   0.4943   0.02550   0.01272  -0.0115   0.0815   1.0000
   4.250   0.5175   0.02679   0.01415  -0.0105   0.0634   1.0000
   4.500   0.5460   0.02847   0.01605  -0.0102   0.0552   1.0000
   4.750   0.5737   0.02989   0.01779  -0.0096   0.0467   1.0000
   5.000   0.5988   0.03189   0.01987  -0.0091   0.0417   1.0000
   5.250   0.6249   0.03416   0.02261  -0.0079   0.0402   1.0000
   5.500   0.6473   0.03672   0.02567  -0.0063   0.0391   1.0000
   5.750   0.6657   0.03948   0.02895  -0.0041   0.0384   1.0000
   6.000   0.6805   0.04242   0.03237  -0.0014   0.0381   1.0000
   6.250   0.6918   0.04548   0.03590   0.0015   0.0380   1.0000
   6.500   0.7002   0.04865   0.03950   0.0047   0.0381   1.0000
   6.750   0.7057   0.05191   0.04315   0.0080   0.0382   1.0000
   7.000   0.7085   0.05518   0.04679   0.0114   0.0381   1.0000
   7.250   0.7088   0.05845   0.05039   0.0148   0.0377   1.0000
   7.500   0.7068   0.06175   0.05396   0.0181   0.0371   1.0000
   7.750   0.7026   0.06507   0.05751   0.0213   0.0367   1.0000
   8.000   0.6961   0.06842   0.06104   0.0243   0.0363   1.0000
   8.250   0.6873   0.07181   0.06457   0.0271   0.0362   1.0000
   8.500   0.6765   0.07525   0.06811   0.0296   0.0363   1.0000
   8.750   0.6637   0.07875   0.07167   0.0317   0.0365   1.0000
   9.000   0.6482   0.08214   0.07507   0.0337   0.0370   1.0000
   9.250   0.6341   0.08599   0.07893   0.0342   0.0376   1.0000
   9.500   0.6226   0.09042   0.08334   0.0331   0.0382   1.0000
   9.750   0.6142   0.09539   0.08827   0.0307   0.0388   1.0000
  10.000   0.6089   0.10057   0.09340   0.0278   0.0393   1.0000
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