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NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il)
Reynolds number: 500,000
Max Cl/Cd: 110.53 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n2h15-il-500000.txt
Download as CSV file: xf-n2h15-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2-H-15 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0988   0.08916   0.08568  -0.0885   0.7093   0.0290
 -10.000  -0.0977   0.08661   0.08315  -0.0890   0.7083   0.0292
  -9.750  -0.0975   0.08405   0.08059  -0.0895   0.7074   0.0298
  -9.500  -0.0989   0.08139   0.07795  -0.0901   0.7066   0.0303
  -9.250  -0.1020   0.07863   0.07521  -0.0907   0.7057   0.0308
  -9.000  -0.1137   0.07520   0.07180  -0.0921   0.7048   0.0317
  -8.750  -0.1363   0.07115   0.06778  -0.0947   0.7038   0.0321
  -8.500  -0.1589   0.06784   0.06444  -0.0944   0.7028   0.0322
  -8.250  -0.1872   0.06496   0.06148  -0.0910   0.7015   0.0324
  -8.000  -0.2106   0.06275   0.05924  -0.0860   0.6998   0.0325
  -7.750  -0.2267   0.06108   0.05753  -0.0811   0.6979   0.0325
  -7.500  -0.2469   0.05769   0.05406  -0.0764   0.6963   0.0326
  -7.250  -0.2471   0.05519   0.05157  -0.0741   0.6949   0.0329
  -7.000  -0.2450   0.05348   0.04985  -0.0716   0.6937   0.0331
  -6.750  -0.2428   0.05178   0.04811  -0.0689   0.6925   0.0333
  -6.500  -0.2407   0.04996   0.04621  -0.0660   0.6914   0.0334
  -6.250  -0.2360   0.04836   0.04455  -0.0633   0.6905   0.0338
  -6.000  -0.2306   0.04675   0.04286  -0.0605   0.6896   0.0342
  -5.750  -0.2250   0.04503   0.04103  -0.0575   0.6887   0.0348
  -5.500  -0.2192   0.04317   0.03904  -0.0543   0.6879   0.0353
  -5.250  -0.2130   0.04128   0.03698  -0.0508   0.6870   0.0365
  -5.000  -0.2128   0.04047   0.03561  -0.0438   0.6857   0.0386
  -4.750  -0.2175   0.03682   0.03183  -0.0391   0.6832   0.0392
  -4.500  -0.2040   0.03525   0.03028  -0.0374   0.6810   0.0396
  -4.250  -0.1905   0.03409   0.02908  -0.0354   0.6794   0.0400
  -4.000  -0.1757   0.03305   0.02799  -0.0334   0.6780   0.0406
  -3.750  -0.1610   0.03198   0.02684  -0.0311   0.6768   0.0415
  -3.500  -0.1453   0.03092   0.02564  -0.0288   0.6758   0.0430
  -3.250  -0.1296   0.03191   0.02619  -0.0246   0.6748   0.0459
  -3.000  -0.1198   0.02804   0.02217  -0.0217   0.6740   0.0473
  -2.750  -0.0989   0.02687   0.02096  -0.0206   0.6733   0.0481
  -2.500  -0.0778   0.02599   0.02001  -0.0194   0.6726   0.0497
  -2.250  -0.0564   0.02529   0.01917  -0.0179   0.6720   0.0520
  -2.000  -0.0395   0.02441   0.01796  -0.0152   0.6712   0.0566
  -1.750  -0.0231   0.02441   0.01812  -0.0146   0.6659   0.0579
  -1.500  -0.0005   0.02391   0.01759  -0.0139   0.6637   0.0600
  -1.250   0.0198   0.02417   0.01774  -0.0121   0.6623   0.0645
  -1.000   0.0769   0.02094   0.01396  -0.0167   0.6620   0.0468
  -0.750   0.1580   0.01852   0.01145  -0.0281   0.6620   0.0405
  -0.500   0.2146   0.01753   0.01046  -0.0345   0.6615   0.0406
  -0.250   0.2549   0.01696   0.00989  -0.0374   0.6607   0.0405
   0.000   0.2896   0.01655   0.00949  -0.0390   0.6600   0.0413
   0.250   0.3208   0.01623   0.00919  -0.0398   0.6593   0.0423
   0.500   0.3509   0.01594   0.00890  -0.0404   0.6587   0.0433
   0.750   0.3804   0.01568   0.00863  -0.0408   0.6580   0.0448
   1.000   0.4099   0.01543   0.00838  -0.0411   0.6574   0.0458
   1.250   0.4403   0.01516   0.00810  -0.0417   0.6568   0.0474
   1.500   0.4697   0.01503   0.00798  -0.0422   0.6562   0.0506
   1.750   0.4840   0.01654   0.00964  -0.0416   0.6494   0.0531
   2.000   0.5121   0.01655   0.00970  -0.0419   0.6479   0.0640
   2.250   0.7737   0.01471   0.01025  -0.0908   0.6558   0.9937
   2.500   0.8272   0.01493   0.01057  -0.0973   0.6524   0.9995
   2.750   0.8482   0.01527   0.01096  -0.0970   0.6496   1.0000
   3.000   0.8693   0.01540   0.01110  -0.0962   0.6478   1.0000
   3.250   0.8926   0.01546   0.01116  -0.0956   0.6465   1.0000
   3.500   0.9172   0.01544   0.01114  -0.0952   0.6454   1.0000
   3.750   0.9431   0.01528   0.01097  -0.0949   0.6445   1.0000
   4.000   0.9706   0.01488   0.01054  -0.0947   0.6435   1.0000
   4.250   1.0006   0.01405   0.00966  -0.0945   0.6422   1.0000
   4.500   1.0289   0.01366   0.00922  -0.0943   0.6409   1.0000
   4.750   1.0514   0.01401   0.00970  -0.0940   0.6359   1.0000
   5.000   1.0790   0.01366   0.00936  -0.0939   0.6325   1.0000
   5.250   1.1111   0.01255   0.00818  -0.0939   0.6285   1.0000
   5.500   1.1391   0.01207   0.00770  -0.0938   0.6222   1.0000
   5.750   1.1671   0.01167   0.00732  -0.0938   0.6149   1.0000
   6.000   1.1943   0.01144   0.00710  -0.0937   0.6083   1.0000
   6.250   1.2206   0.01136   0.00708  -0.0936   0.5989   1.0000
   6.500   1.2466   0.01134   0.00709  -0.0935   0.5844   1.0000
   6.750   1.2711   0.01150   0.00722  -0.0933   0.5561   1.0000
   7.000   1.2800   0.01360   0.00883  -0.0924   0.4621   1.0000
   7.250   1.2522   0.01796   0.01285  -0.0879   0.3960   1.0000
   7.500   1.2178   0.02022   0.01503  -0.0790   0.3764   1.0000
   7.750   1.1815   0.02330   0.01790  -0.0713   0.3357   1.0000
   8.000   1.1509   0.02650   0.02081  -0.0649   0.2861   1.0000
   8.250   1.1242   0.02983   0.02379  -0.0595   0.2239   1.0000
   8.500   1.1019   0.03313   0.02666  -0.0550   0.1525   1.0000
   8.750   1.0915   0.03576   0.02895  -0.0518   0.0994   1.0000
   9.000   1.0876   0.03800   0.03093  -0.0493   0.0621   1.0000
   9.250   1.0941   0.03954   0.03242  -0.0477   0.0519   1.0000
   9.500   1.1038   0.04085   0.03372  -0.0464   0.0473   1.0000
   9.750   1.1115   0.04234   0.03520  -0.0449   0.0437   1.0000
  10.000   1.1225   0.04361   0.03650  -0.0438   0.0413   1.0000
  10.250   1.1326   0.04494   0.03787  -0.0427   0.0394   1.0000
  10.500   1.1374   0.04675   0.03967  -0.0411   0.0368   1.0000
  10.750   1.1488   0.04801   0.04098  -0.0402   0.0357   1.0000
  11.000   1.1592   0.04939   0.04240  -0.0392   0.0345   1.0000
  11.250   1.1691   0.05081   0.04384  -0.0381   0.0329   1.0000
  11.500   1.1773   0.05238   0.04542  -0.0370   0.0318   1.0000
  11.750   1.1794   0.05448   0.04755  -0.0355   0.0305   1.0000
  12.000   1.1910   0.05581   0.04893  -0.0347   0.0299   1.0000
  12.250   1.2016   0.05720   0.05038  -0.0338   0.0289   1.0000
  12.500   1.2131   0.05851   0.05172  -0.0330   0.0279   1.0000
  12.750   1.2226   0.05999   0.05323  -0.0321   0.0270   1.0000
  13.000   1.2324   0.06147   0.05474  -0.0313   0.0266   1.0000
  13.250   1.2387   0.06309   0.05634  -0.0299   0.0255   1.0000
  13.500   1.2494   0.06438   0.05769  -0.0289   0.0250   1.0000
  13.750   1.2609   0.06576   0.05914  -0.0282   0.0243   1.0000
  14.000   1.2720   0.06714   0.06059  -0.0276   0.0236   1.0000
  14.250   1.2830   0.06848   0.06197  -0.0268   0.0230   1.0000
  14.500   1.2938   0.06986   0.06339  -0.0261   0.0224   1.0000
  14.750   1.3038   0.07135   0.06489  -0.0254   0.0218   1.0000
  15.000   1.3158   0.07231   0.06583  -0.0243   0.0211   1.0000
  15.250   1.3289   0.07322   0.06680  -0.0232   0.0207   1.0000
  15.500   1.3378   0.07493   0.06863  -0.0226   0.0203   1.0000
  15.750   1.3481   0.07637   0.07017  -0.0218   0.0199   1.0000
  16.000   1.3593   0.07767   0.07156  -0.0210   0.0197   1.0000
  16.250   1.3671   0.07950   0.07349  -0.0204   0.0192   1.0000
  16.500   1.3747   0.08137   0.07544  -0.0199   0.0187   1.0000
  16.750   1.3814   0.08335   0.07750  -0.0194   0.0183   1.0000
  17.000   1.3889   0.08517   0.07941  -0.0188   0.0181   1.0000
  17.250   1.3949   0.08724   0.08155  -0.0184   0.0179   1.0000
  17.500   1.4013   0.08917   0.08347  -0.0181   0.0174   1.0000
  17.750   1.4120   0.09041   0.08481  -0.0167   0.0170   1.0000
  18.000   1.4088   0.09386   0.08846  -0.0165   0.0169   1.0000
  18.250   1.4052   0.09741   0.09219  -0.0166   0.0167   1.0000
  18.500   1.4012   0.10108   0.09604  -0.0167   0.0164   1.0000
  18.750   1.3965   0.10484   0.10000  -0.0168   0.0163   1.0000
  19.000   1.3878   0.10934   0.10471  -0.0173   0.0160   1.0000
  19.250   1.3791   0.11392   0.10948  -0.0178   0.0160   1.0000
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