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NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-012 (naca16012-il)
Reynolds number: 50,000
Max Cl/Cd: 22.09 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16012-il-50000-n5.txt
Download as CSV file: xf-naca16012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-012                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6613   0.09230   0.08497  -0.0522   1.0000   0.0431
 -11.000  -0.6789   0.08799   0.08064  -0.0519   1.0000   0.0429
 -10.750  -0.6985   0.08413   0.07673  -0.0506   1.0000   0.0427
 -10.500  -0.7192   0.08073   0.07328  -0.0481   1.0000   0.0426
 -10.250  -0.7410   0.07777   0.07025  -0.0445   1.0000   0.0424
 -10.000  -0.7633   0.07522   0.06763  -0.0396   1.0000   0.0423
  -9.750  -0.7844   0.07271   0.06501  -0.0343   1.0000   0.0423
  -9.500  -0.8021   0.06985   0.06199  -0.0294   1.0000   0.0422
  -9.250  -0.8176   0.06697   0.05891  -0.0243   1.0000   0.0423
  -9.000  -0.8314   0.06408   0.05574  -0.0190   1.0000   0.0425
  -8.750  -0.8432   0.06124   0.05254  -0.0137   1.0000   0.0429
  -8.500  -0.8503   0.05818   0.04924  -0.0091   1.0000   0.0437
  -8.250  -0.8491   0.05568   0.04658  -0.0058   1.0000   0.0454
  -8.000  -0.8469   0.05337   0.04407  -0.0023   1.0000   0.0470
  -7.750  -0.8446   0.05074   0.04110   0.0016   1.0000   0.0484
  -7.500  -0.8394   0.04792   0.03787   0.0053   1.0000   0.0495
  -7.250  -0.8306   0.04520   0.03470   0.0086   1.0000   0.0512
  -7.000  -0.8190   0.04284   0.03175   0.0117   1.0000   0.0544
  -6.750  -0.8028   0.04041   0.02903   0.0136   1.0000   0.0578
  -6.500  -0.7820   0.03831   0.02670   0.0149   1.0000   0.0611
  -6.250  -0.7597   0.03658   0.02459   0.0161   1.0000   0.0671
  -6.000  -0.7327   0.03477   0.02265   0.0162   1.0000   0.0733
  -5.750  -0.7012   0.03330   0.02086   0.0158   1.0000   0.0806
  -5.500  -0.6722   0.03206   0.01957   0.0155   1.0000   0.0908
  -5.250  -0.6404   0.03086   0.01817   0.0151   1.0000   0.0993
  -5.000  -0.6184   0.02984   0.01702   0.0162   1.0000   0.1097
  -4.750  -0.6009   0.02883   0.01600   0.0179   1.0000   0.1265
  -4.500  -0.5862   0.02766   0.01506   0.0200   1.0000   0.1577
  -4.250  -0.5760   0.02609   0.01406   0.0227   1.0000   0.2328
  -4.000  -0.4895   0.02660   0.01719   0.0174   1.0000   0.8241
  -3.750  -0.3486   0.03088   0.02056   0.0014   1.0000   0.9281
  -3.500  -0.2900   0.03108   0.02032  -0.0049   1.0000   0.9519
  -3.250  -0.2487   0.03082   0.01976  -0.0084   1.0000   0.9645
  -3.000  -0.2100   0.03045   0.01913  -0.0117   1.0000   0.9742
  -2.750  -0.1731   0.03006   0.01853  -0.0147   1.0000   0.9830
  -2.500  -0.1367   0.02967   0.01796  -0.0176   1.0000   0.9911
  -2.250  -0.1001   0.02929   0.01742  -0.0206   1.0000   0.9986
  -2.000  -0.0845   0.02907   0.01710  -0.0194   1.0000   1.0000
  -1.750  -0.0740   0.02889   0.01686  -0.0170   1.0000   1.0000
  -1.500  -0.0635   0.02874   0.01664  -0.0146   1.0000   1.0000
  -1.250  -0.0529   0.02861   0.01646  -0.0122   1.0000   1.0000
  -1.000  -0.0424   0.02851   0.01632  -0.0098   1.0000   1.0000
  -0.750  -0.0318   0.02843   0.01621  -0.0073   1.0000   1.0000
  -0.500  -0.0212   0.02837   0.01613  -0.0049   1.0000   1.0000
  -0.250  -0.0106   0.02834   0.01609  -0.0025   1.0000   1.0000
   0.000   0.0000   0.02833   0.01607   0.0000   1.0000   1.0000
   0.250   0.0106   0.02834   0.01608   0.0025   1.0000   1.0000
   0.500   0.0212   0.02837   0.01613   0.0049   1.0000   1.0000
   0.750   0.0318   0.02843   0.01621   0.0073   1.0000   1.0000
   1.000   0.0424   0.02850   0.01632   0.0098   1.0000   1.0000
   1.250   0.0529   0.02860   0.01646   0.0122   1.0000   1.0000
   1.500   0.0635   0.02873   0.01663   0.0146   1.0000   1.0000
   1.750   0.0740   0.02888   0.01685   0.0170   1.0000   1.0000
   2.000   0.0845   0.02906   0.01709   0.0194   1.0000   1.0000
   2.250   0.1000   0.02928   0.01740   0.0207   0.9987   1.0000
   2.500   0.1366   0.02966   0.01795   0.0176   0.9911   1.0000
   2.750   0.1730   0.03005   0.01852   0.0147   0.9831   1.0000
   3.000   0.2099   0.03043   0.01911   0.0117   0.9743   1.0000
   3.250   0.2486   0.03080   0.01974   0.0085   0.9645   1.0000
   3.500   0.2898   0.03106   0.02030   0.0049   0.9520   1.0000
   3.750   0.3483   0.03087   0.02054  -0.0013   0.9282   1.0000
   4.000   0.4896   0.02659   0.01718  -0.0174   0.8241   1.0000
   4.250   0.5760   0.02608   0.01405  -0.0227   0.2329   1.0000
   4.500   0.5861   0.02766   0.01505  -0.0200   0.1578   1.0000
   4.750   0.6009   0.02882   0.01600  -0.0179   0.1265   1.0000
   5.000   0.6184   0.02983   0.01701  -0.0162   0.1098   1.0000
   5.250   0.6404   0.03085   0.01816  -0.0150   0.0994   1.0000
   5.500   0.6721   0.03205   0.01957  -0.0155   0.0908   1.0000
   5.750   0.7011   0.03329   0.02085  -0.0158   0.0806   1.0000
   6.000   0.7326   0.03477   0.02264  -0.0162   0.0733   1.0000
   6.250   0.7596   0.03657   0.02458  -0.0161   0.0671   1.0000
   6.500   0.7819   0.03830   0.02669  -0.0149   0.0611   1.0000
   6.750   0.8027   0.04040   0.02902  -0.0136   0.0578   1.0000
   7.000   0.8190   0.04283   0.03174  -0.0117   0.0545   1.0000
   7.250   0.8305   0.04520   0.03469  -0.0086   0.0512   1.0000
   7.500   0.8394   0.04791   0.03786  -0.0053   0.0495   1.0000
   7.750   0.8445   0.05073   0.04109  -0.0016   0.0484   1.0000
   8.000   0.8469   0.05337   0.04407   0.0023   0.0471   1.0000
   8.250   0.8492   0.05566   0.04656   0.0058   0.0454   1.0000
   8.500   0.8503   0.05817   0.04923   0.0091   0.0438   1.0000
   8.750   0.8432   0.06123   0.05253   0.0137   0.0429   1.0000
   9.000   0.8315   0.06407   0.05573   0.0190   0.0425   1.0000
   9.250   0.8177   0.06697   0.05890   0.0243   0.0423   1.0000
   9.500   0.8022   0.06985   0.06199   0.0293   0.0422   1.0000
   9.750   0.7846   0.07270   0.06500   0.0343   0.0423   1.0000
  10.000   0.7635   0.07523   0.06763   0.0396   0.0423   1.0000
  10.250   0.7411   0.07779   0.07027   0.0444   0.0424   1.0000
  10.500   0.7195   0.08074   0.07329   0.0481   0.0426   1.0000
  10.750   0.6988   0.08414   0.07674   0.0506   0.0427   1.0000
  11.000   0.6793   0.08800   0.08064   0.0519   0.0429   1.0000
  11.250   0.6618   0.09230   0.08497   0.0521   0.0431   1.0000
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