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NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il)
Reynolds number: 200,000
Max Cl/Cd: 31.12 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n1h15-il-200000-n5.txt
Download as CSV file: xf-n1h15-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1-H-15 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2141   0.10828   0.10392  -0.0526   0.7207   0.0367
 -10.250  -0.2185   0.10484   0.10048  -0.0558   0.7201   0.0388
 -10.000  -0.2242   0.10054   0.09627  -0.0630   0.7171   0.0393
  -9.750  -0.2213   0.09676   0.09253  -0.0669   0.7149   0.0394
  -9.500  -0.2163   0.09285   0.08865  -0.0688   0.7133   0.0396
  -9.250  -0.2032   0.09031   0.08610  -0.0684   0.7120   0.0401
  -9.000  -0.1949   0.08769   0.08348  -0.0691   0.7108   0.0406
  -8.750  -0.1907   0.08480   0.08059  -0.0706   0.7095   0.0410
  -8.500  -0.1874   0.08196   0.07775  -0.0720   0.7084   0.0418
  -8.250  -0.1894   0.07867   0.07446  -0.0743   0.7074   0.0424
  -8.000  -0.1939   0.07565   0.07142  -0.0759   0.7064   0.0435
  -7.750  -0.2180   0.07106   0.06667  -0.0798   0.7053   0.0466
  -7.500  -0.2202   0.06686   0.06224  -0.0840   0.7010   0.0469
  -7.250  -0.2139   0.06362   0.05884  -0.0854   0.6975   0.0470
  -7.000  -0.2011   0.05923   0.05456  -0.0850   0.6960   0.0386
  -6.750  -0.1929   0.05675   0.05200  -0.0845   0.6946   0.0376
  -6.500  -0.1866   0.05352   0.04860  -0.0837   0.6934   0.0365
  -6.250  -0.1803   0.05002   0.04485  -0.0824   0.6924   0.0359
  -6.000  -0.1709   0.04712   0.04171  -0.0809   0.6916   0.0363
  -5.750  -0.1609   0.04417   0.03848  -0.0791   0.6909   0.0364
  -5.500  -0.1485   0.04255   0.03662  -0.0799   0.6842   0.0357
  -5.250  -0.1383   0.04001   0.03373  -0.0780   0.6815   0.0353
  -5.000  -0.1258   0.03776   0.03112  -0.0758   0.6798   0.0351
  -4.750  -0.1109   0.03586   0.02889  -0.0738   0.6786   0.0351
  -4.500  -0.0936   0.03433   0.02708  -0.0721   0.6777   0.0353
  -4.250  -0.0741   0.03317   0.02569  -0.0708   0.6769   0.0361
  -4.000  -0.0538   0.03191   0.02415  -0.0694   0.6763   0.0367
  -3.750  -0.0479   0.03262   0.02474  -0.0683   0.6687   0.0368
  -3.500  -0.0291   0.03179   0.02368  -0.0670   0.6666   0.0368
  -3.250  -0.0082   0.03098   0.02265  -0.0659   0.6652   0.0370
  -3.000   0.0144   0.03025   0.02174  -0.0650   0.6641   0.0373
  -2.750   0.0382   0.02958   0.02090  -0.0643   0.6633   0.0376
  -2.500   0.0629   0.02896   0.02015  -0.0638   0.6625   0.0379
  -2.250   0.0880   0.02842   0.01950  -0.0633   0.6619   0.0384
  -2.000   0.0786   0.02987   0.02093  -0.0593   0.6533   0.0386
  -1.750   0.0983   0.02976   0.02073  -0.0582   0.6516   0.0392
  -1.500   0.1200   0.02938   0.02034  -0.0574   0.6504   0.0402
  -1.250   0.1423   0.02907   0.02004  -0.0566   0.6493   0.0410
  -1.000   0.1653   0.02878   0.01973  -0.0558   0.6485   0.0416
  -0.750   0.1890   0.02847   0.01942  -0.0551   0.6478   0.0423
  -0.500   0.1624   0.03006   0.02100  -0.0476   0.6388   0.0424
  -0.250   0.1807   0.03007   0.02100  -0.0462   0.6371   0.0431
   0.000   0.2018   0.02998   0.02090  -0.0452   0.6358   0.0439
   0.250   0.2242   0.02986   0.02076  -0.0443   0.6347   0.0449
   0.500   0.2480   0.02972   0.02058  -0.0436   0.6339   0.0460
   0.750   0.2730   0.02952   0.02037  -0.0431   0.6332   0.0478
   1.000   0.2981   0.02936   0.02022  -0.0426   0.6326   0.0514
   1.500   0.5953   0.02921   0.02291  -0.0945   0.6349   1.0000
   1.750   0.6147   0.02929   0.02293  -0.0931   0.6339   1.0000
   2.000   0.6350   0.02935   0.02292  -0.0919   0.6332   1.0000
   2.250   0.6569   0.02934   0.02287  -0.0908   0.6325   1.0000
   2.750   0.6271   0.03192   0.02541  -0.0789   0.6200   1.0000
   3.250   0.6260   0.03407   0.02752  -0.0718   0.6100   1.0000
   3.500   0.6436   0.03437   0.02780  -0.0704   0.6080   1.0000
   3.750   0.6648   0.03448   0.02789  -0.0695   0.6065   1.0000
   4.000   0.6874   0.03453   0.02792  -0.0687   0.6054   1.0000
   4.250   0.7108   0.03456   0.02794  -0.0680   0.6045   1.0000
   4.500   0.7346   0.03458   0.02797  -0.0674   0.6038   1.0000
   5.000   0.7358   0.03713   0.03054  -0.0614   0.5918   1.0000
   5.250   0.7593   0.03717   0.03058  -0.0608   0.5907   1.0000
   5.500   0.7838   0.03714   0.03057  -0.0603   0.5898   1.0000
   5.750   0.8089   0.03708   0.03055  -0.0599   0.5891   1.0000
   6.250   0.8158   0.03955   0.03308  -0.0550   0.5767   1.0000
   6.500   0.8472   0.03878   0.03234  -0.0549   0.5754   1.0000
   6.750   0.8744   0.03825   0.03186  -0.0545   0.5733   1.0000
   8.250   0.9824   0.03773   0.03160  -0.0468   0.5301   1.0000
   8.750   1.0109   0.03847   0.03241  -0.0439   0.4988   1.0000
   9.000   1.0499   0.03654   0.03039  -0.0440   0.4652   1.0000
   9.250   1.0757   0.03457   0.02732  -0.0417   0.3325   1.0000
   9.500   1.0435   0.03849   0.03060  -0.0364   0.2434   1.0000
   9.750   1.0248   0.04173   0.03338  -0.0328   0.1749   1.0000
  10.000   1.0192   0.04411   0.03550  -0.0304   0.1304   1.0000
  10.250   1.0183   0.04617   0.03734  -0.0284   0.0971   1.0000
  10.500   1.0219   0.04794   0.03900  -0.0268   0.0771   1.0000
  10.750   1.0284   0.04951   0.04052  -0.0254   0.0669   1.0000
  11.000   1.0362   0.05099   0.04197  -0.0241   0.0612   1.0000
  11.250   1.0445   0.05245   0.04347  -0.0230   0.0571   1.0000
  11.500   1.0532   0.05391   0.04497  -0.0219   0.0542   1.0000
  11.750   1.0608   0.05548   0.04654  -0.0208   0.0516   1.0000
  12.000   1.0678   0.05713   0.04821  -0.0197   0.0498   1.0000
  12.250   1.0769   0.05859   0.04975  -0.0187   0.0484   1.0000
  12.500   1.0860   0.06008   0.05132  -0.0178   0.0468   1.0000
  12.750   1.0946   0.06161   0.05290  -0.0169   0.0453   1.0000
  13.000   1.1029   0.06319   0.05451  -0.0160   0.0439   1.0000
  13.250   1.1098   0.06489   0.05623  -0.0151   0.0426   1.0000
  13.500   1.1163   0.06659   0.05794  -0.0140   0.0415   1.0000
  13.750   1.1269   0.06795   0.05941  -0.0133   0.0403   1.0000
  14.000   1.1371   0.06935   0.06089  -0.0125   0.0393   1.0000
  14.250   1.1469   0.07078   0.06237  -0.0118   0.0381   1.0000
  14.500   1.1565   0.07224   0.06388  -0.0111   0.0370   1.0000
  14.750   1.1658   0.07374   0.06542  -0.0104   0.0359   1.0000
  15.000   1.1747   0.07519   0.06686  -0.0096   0.0347   1.0000
  15.250   1.1853   0.07646   0.06819  -0.0089   0.0338   1.0000
  15.500   1.1959   0.07784   0.06970  -0.0082   0.0329   1.0000
  15.750   1.2066   0.07919   0.07114  -0.0076   0.0320   1.0000
  16.000   1.2156   0.08079   0.07283  -0.0071   0.0307   1.0000
  16.250   1.2250   0.08232   0.07443  -0.0066   0.0299   1.0000
  16.500   1.2330   0.08402   0.07616  -0.0061   0.0290   1.0000
  16.750   1.2432   0.08530   0.07743  -0.0054   0.0281   1.0000
  17.000   1.2507   0.08716   0.07948  -0.0050   0.0274   1.0000
  17.250   1.2575   0.08911   0.08159  -0.0046   0.0265   1.0000
  17.500   1.2633   0.09119   0.08382  -0.0043   0.0257   1.0000
  17.750   1.2684   0.09338   0.08613  -0.0041   0.0249   1.0000
  18.000   1.2725   0.09572   0.08855  -0.0041   0.0242   1.0000
  18.250   1.2771   0.09794   0.09082  -0.0040   0.0236   1.0000
  18.500   1.2825   0.09999   0.09290  -0.0039   0.0231   1.0000
  18.750   1.2823   0.10305   0.09621  -0.0039   0.0225   1.0000
  19.000   1.2819   0.10616   0.09955  -0.0040   0.0220   1.0000
  19.250   1.2798   0.10955   0.10315  -0.0043   0.0213   1.0000
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