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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 200,000
Max Cl/Cd: 47.31 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1408-il-200000-n5.txt
Download as CSV file: xf-naca1408-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6907   0.07910   0.07571  -0.0094   1.0000   0.0140
  -9.500  -0.7449   0.05639   0.05287  -0.0284   1.0000   0.0130
  -9.250  -0.7649   0.04811   0.04420  -0.0322   1.0000   0.0129
  -9.000  -0.7740   0.04139   0.03698  -0.0331   1.0000   0.0131
  -8.750  -0.7739   0.03597   0.03098  -0.0327   1.0000   0.0134
  -8.500  -0.7661   0.03192   0.02641  -0.0319   1.0000   0.0139
  -8.250  -0.7503   0.02964   0.02385  -0.0311   1.0000   0.0144
  -8.000  -0.7319   0.02783   0.02177  -0.0304   1.0000   0.0151
  -7.750  -0.7127   0.02602   0.01967  -0.0295   1.0000   0.0160
  -7.500  -0.6920   0.02453   0.01789  -0.0287   1.0000   0.0175
  -7.250  -0.6706   0.02301   0.01604  -0.0278   1.0000   0.0191
  -7.000  -0.6493   0.02138   0.01413  -0.0268   1.0000   0.0204
  -6.750  -0.6280   0.02009   0.01274  -0.0260   1.0000   0.0220
  -6.500  -0.6051   0.01941   0.01192  -0.0253   1.0000   0.0244
  -6.250  -0.5819   0.01861   0.01096  -0.0245   1.0000   0.0275
  -6.000  -0.5587   0.01781   0.00998  -0.0236   1.0000   0.0295
  -5.750  -0.5370   0.01681   0.00897  -0.0227   1.0000   0.0330
  -5.500  -0.5137   0.01624   0.00831  -0.0220   1.0000   0.0366
  -5.250  -0.4901   0.01572   0.00765  -0.0211   1.0000   0.0394
  -5.000  -0.4678   0.01490   0.00683  -0.0203   1.0000   0.0435
  -4.750  -0.4444   0.01442   0.00630  -0.0196   1.0000   0.0471
  -4.500  -0.4207   0.01401   0.00581  -0.0188   1.0000   0.0507
  -4.250  -0.3974   0.01347   0.00523  -0.0180   1.0000   0.0540
  -4.000  -0.3737   0.01305   0.00477  -0.0173   1.0000   0.0582
  -3.750  -0.3497   0.01271   0.00438  -0.0166   1.0000   0.0636
  -3.500  -0.3257   0.01232   0.00405  -0.0160   1.0000   0.0756
  -3.250  -0.3016   0.01192   0.00375  -0.0155   1.0000   0.0979
  -3.000  -0.2774   0.01154   0.00350  -0.0150   1.0000   0.1333
  -2.750  -0.2426   0.01112   0.00328  -0.0169   0.9959   0.1858
  -2.500  -0.2071   0.01072   0.00309  -0.0188   0.9906   0.2454
  -2.250  -0.1708   0.01030   0.00294  -0.0210   0.9858   0.3180
  -2.000  -0.1376   0.00975   0.00282  -0.0225   0.9791   0.4244
  -1.750  -0.1048   0.00914   0.00277  -0.0237   0.9730   0.5583
  -1.500  -0.0742   0.00866   0.00274  -0.0241   0.9655   0.6751
  -1.250  -0.0460   0.00831   0.00277  -0.0236   0.9565   0.7754
  -1.000  -0.0142   0.00815   0.00280  -0.0236   0.9486   0.8558
  -0.750   0.0224   0.00810   0.00280  -0.0249   0.9392   0.9109
  -0.500   0.0641   0.00807   0.00276  -0.0274   0.9299   0.9485
  -0.250   0.1075   0.00803   0.00269  -0.0305   0.9193   0.9735
   0.000   0.1508   0.00798   0.00261  -0.0337   0.9057   0.9908
   0.250   0.1894   0.00793   0.00252  -0.0358   0.8875   1.0000
   0.500   0.2171   0.00791   0.00243  -0.0355   0.8649   1.0000
   0.750   0.2431   0.00791   0.00236  -0.0348   0.8392   1.0000
   1.000   0.2685   0.00795   0.00232  -0.0340   0.8121   1.0000
   1.250   0.2935   0.00802   0.00229  -0.0331   0.7833   1.0000
   1.500   0.3182   0.00813   0.00228  -0.0322   0.7524   1.0000
   1.750   0.3427   0.00827   0.00230  -0.0313   0.7182   1.0000
   2.000   0.3671   0.00845   0.00234  -0.0303   0.6817   1.0000
   2.250   0.3914   0.00866   0.00240  -0.0294   0.6445   1.0000
   2.500   0.4148   0.00894   0.00249  -0.0283   0.5936   1.0000
   2.750   0.4375   0.00934   0.00257  -0.0272   0.5277   1.0000
   3.000   0.4602   0.00978   0.00270  -0.0262   0.4585   1.0000
   3.250   0.4835   0.01022   0.00289  -0.0254   0.3945   1.0000
   3.500   0.5068   0.01072   0.00310  -0.0247   0.3268   1.0000
   3.750   0.5306   0.01123   0.00337  -0.0241   0.2658   1.0000
   4.000   0.5541   0.01182   0.00369  -0.0235   0.2034   1.0000
   4.250   0.5775   0.01247   0.00410  -0.0229   0.1445   1.0000
   4.500   0.6010   0.01314   0.00454  -0.0224   0.0974   1.0000
   4.750   0.6249   0.01376   0.00505  -0.0218   0.0717   1.0000
   5.000   0.6494   0.01430   0.00557  -0.0213   0.0603   1.0000
   5.250   0.6741   0.01480   0.00613  -0.0207   0.0540   1.0000
   5.500   0.6985   0.01534   0.00672  -0.0202   0.0499   1.0000
   5.750   0.7216   0.01609   0.00750  -0.0195   0.0461   1.0000
   6.000   0.7460   0.01662   0.00813  -0.0189   0.0431   1.0000
   6.250   0.7699   0.01722   0.00884  -0.0183   0.0397   1.0000
   6.500   0.7925   0.01804   0.00967  -0.0176   0.0358   1.0000
   6.750   0.8153   0.01888   0.01063  -0.0169   0.0330   1.0000
   7.000   0.8389   0.01956   0.01143  -0.0162   0.0295   1.0000
   7.250   0.8613   0.02040   0.01231  -0.0156   0.0265   1.0000
   7.500   0.8821   0.02171   0.01373  -0.0146   0.0243   1.0000
   7.750   0.9052   0.02256   0.01481  -0.0139   0.0217   1.0000
   8.000   0.9273   0.02351   0.01589  -0.0131   0.0194   1.0000
   8.250   0.9486   0.02455   0.01704  -0.0124   0.0179   1.0000
   8.500   0.9664   0.02646   0.01908  -0.0113   0.0166   1.0000
   8.750   0.9867   0.02788   0.02077  -0.0103   0.0156   1.0000
   9.000   1.0057   0.02943   0.02261  -0.0092   0.0143   1.0000
   9.250   1.0227   0.03123   0.02468  -0.0081   0.0134   1.0000
   9.500   1.0379   0.03317   0.02689  -0.0068   0.0127   1.0000
   9.750   1.0514   0.03513   0.02910  -0.0055   0.0122   1.0000
  10.000   1.0624   0.03724   0.03150  -0.0042   0.0118   1.0000
  10.250   1.0687   0.03984   0.03438  -0.0025   0.0115   1.0000
  10.500   1.0670   0.04328   0.03816  -0.0006   0.0112   1.0000
  11.000   1.0400   0.05104   0.04657   0.0038   0.0109   1.0000
  11.250   1.0225   0.05542   0.05122   0.0040   0.0108   1.0000
  11.500   1.0029   0.06093   0.05698   0.0017   0.0109   1.0000
  11.750   0.9819   0.06801   0.06426  -0.0032   0.0109   1.0000
  12.000   0.8597   0.10862   0.10527  -0.0302   0.0127   1.0000
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