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NACA 0008 (naca0008-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0008 (naca0008-il)
Reynolds number: 100,000
Max Cl/Cd: 30.44 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0008-il-100000-n5.txt
Download as CSV file: xf-naca0008-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7704   0.07881   0.07389  -0.0050   1.0000   0.0230
 -10.000  -0.7872   0.07104   0.06603  -0.0120   1.0000   0.0229
  -9.750  -0.8058   0.06521   0.06012  -0.0156   1.0000   0.0227
  -9.500  -0.8228   0.06029   0.05499  -0.0164   1.0000   0.0227
  -9.250  -0.8342   0.05521   0.04957  -0.0166   1.0000   0.0228
  -9.000  -0.8399   0.05033   0.04424  -0.0161   1.0000   0.0230
  -8.750  -0.8390   0.04604   0.03962  -0.0154   1.0000   0.0237
  -8.500  -0.8278   0.04379   0.03718  -0.0148   1.0000   0.0250
  -8.250  -0.8154   0.04131   0.03444  -0.0140   1.0000   0.0265
  -8.000  -0.8032   0.03803   0.03069  -0.0129   1.0000   0.0279
  -7.750  -0.7886   0.03468   0.02681  -0.0117   1.0000   0.0292
  -7.500  -0.7707   0.03193   0.02349  -0.0105   1.0000   0.0314
  -7.250  -0.7514   0.02954   0.02077  -0.0096   1.0000   0.0341
  -7.000  -0.7302   0.02782   0.01891  -0.0089   1.0000   0.0367
  -6.750  -0.7078   0.02621   0.01703  -0.0080   1.0000   0.0403
  -6.500  -0.6849   0.02464   0.01514  -0.0072   1.0000   0.0444
  -6.250  -0.6625   0.02322   0.01369  -0.0065   1.0000   0.0481
  -6.000  -0.6389   0.02225   0.01256  -0.0058   1.0000   0.0536
  -5.750  -0.6161   0.02102   0.01123  -0.0049   1.0000   0.0575
  -5.500  -0.5932   0.02010   0.01029  -0.0042   1.0000   0.0630
  -5.250  -0.5696   0.01930   0.00933  -0.0034   1.0000   0.0687
  -5.000  -0.5474   0.01832   0.00834  -0.0025   1.0000   0.0740
  -4.750  -0.5241   0.01757   0.00750  -0.0016   1.0000   0.0819
  -4.500  -0.5011   0.01677   0.00673  -0.0008   1.0000   0.0950
  -4.250  -0.4783   0.01596   0.00606  -0.0001   1.0000   0.1217
  -4.000  -0.4561   0.01507   0.00549   0.0007   1.0000   0.1823
  -3.750  -0.4340   0.01426   0.00505   0.0014   1.0000   0.2623
  -3.500  -0.4115   0.01362   0.00471   0.0022   1.0000   0.3378
  -3.250  -0.3902   0.01294   0.00447   0.0034   1.0000   0.4369
  -3.000  -0.3696   0.01232   0.00432   0.0050   1.0000   0.5449
  -2.750  -0.3480   0.01188   0.00423   0.0066   1.0000   0.6302
  -2.500  -0.3249   0.01159   0.00416   0.0082   1.0000   0.6980
  -2.250  -0.3017   0.01141   0.00411   0.0098   1.0000   0.7607
  -2.000  -0.2765   0.01131   0.00412   0.0112   1.0000   0.8156
  -1.750  -0.2477   0.01129   0.00412   0.0117   1.0000   0.8626
  -1.500  -0.2131   0.01131   0.00410   0.0108   1.0000   0.9016
  -1.250  -0.1747   0.01135   0.00408   0.0090   1.0000   0.9340
  -1.000  -0.1318   0.01137   0.00402   0.0059   1.0000   0.9592
  -0.750  -0.0864   0.01136   0.00395   0.0022   1.0000   0.9793
  -0.500  -0.0385   0.01132   0.00387  -0.0022   1.0000   0.9954
  -0.250  -0.0137   0.01126   0.00379  -0.0022   1.0000   1.0000
   0.000   0.0000   0.01124   0.00377   0.0000   1.0000   1.0000
   0.250   0.0137   0.01126   0.00379   0.0022   1.0000   1.0000
   0.500   0.0386   0.01132   0.00387   0.0022   0.9954   1.0000
   0.750   0.0864   0.01136   0.00395  -0.0022   0.9793   1.0000
   1.000   0.1318   0.01137   0.00402  -0.0059   0.9592   1.0000
   1.250   0.1747   0.01135   0.00408  -0.0090   0.9340   1.0000
   1.500   0.2131   0.01131   0.00410  -0.0108   0.9016   1.0000
   1.750   0.2477   0.01129   0.00412  -0.0117   0.8626   1.0000
   2.000   0.2765   0.01131   0.00412  -0.0112   0.8156   1.0000
   2.250   0.3017   0.01141   0.00411  -0.0098   0.7607   1.0000
   2.500   0.3249   0.01159   0.00416  -0.0082   0.6980   1.0000
   2.750   0.3480   0.01188   0.00423  -0.0066   0.6301   1.0000
   3.000   0.3696   0.01232   0.00432  -0.0050   0.5449   1.0000
   3.250   0.3902   0.01294   0.00447  -0.0034   0.4369   1.0000
   3.500   0.4115   0.01362   0.00471  -0.0023   0.3377   1.0000
   3.750   0.4341   0.01426   0.00505  -0.0014   0.2623   1.0000
   4.000   0.4561   0.01507   0.00549  -0.0007   0.1823   1.0000
   4.250   0.4783   0.01596   0.00606   0.0001   0.1217   1.0000
   4.500   0.5011   0.01677   0.00673   0.0008   0.0950   1.0000
   4.750   0.5241   0.01757   0.00750   0.0016   0.0819   1.0000
   5.000   0.5474   0.01832   0.00834   0.0025   0.0740   1.0000
   5.250   0.5696   0.01930   0.00933   0.0034   0.0688   1.0000
   5.500   0.5932   0.02010   0.01029   0.0042   0.0630   1.0000
   5.750   0.6161   0.02102   0.01123   0.0049   0.0575   1.0000
   6.000   0.6389   0.02225   0.01256   0.0058   0.0536   1.0000
   6.250   0.6625   0.02321   0.01369   0.0065   0.0480   1.0000
   6.500   0.6849   0.02464   0.01514   0.0072   0.0444   1.0000
   6.750   0.7078   0.02621   0.01703   0.0080   0.0403   1.0000
   7.000   0.7302   0.02782   0.01891   0.0089   0.0367   1.0000
   7.250   0.7514   0.02954   0.02077   0.0096   0.0341   1.0000
   7.500   0.7707   0.03193   0.02349   0.0105   0.0314   1.0000
   7.750   0.7886   0.03468   0.02681   0.0117   0.0292   1.0000
   8.000   0.8032   0.03803   0.03069   0.0129   0.0279   1.0000
   8.250   0.8154   0.04131   0.03443   0.0140   0.0265   1.0000
   8.500   0.8278   0.04378   0.03717   0.0148   0.0250   1.0000
   8.750   0.8390   0.04603   0.03962   0.0154   0.0237   1.0000
   9.000   0.8399   0.05034   0.04424   0.0161   0.0230   1.0000
   9.250   0.8342   0.05522   0.04958   0.0166   0.0227   1.0000
   9.500   0.8228   0.06031   0.05500   0.0164   0.0227   1.0000
   9.750   0.8059   0.06524   0.06016   0.0156   0.0227   1.0000
  10.000   0.7875   0.07108   0.06613   0.0119   0.0229   1.0000
  10.250   0.7706   0.07890   0.07398   0.0049   0.0230   1.0000
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