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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 50,000
Max Cl/Cd: 37.41 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2511-il-50000-n5.txt
Download as CSV file: xf-hq2511-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/11 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4118   0.09867   0.09158  -0.0411   1.0000   0.0441
  -9.500  -0.4122   0.09473   0.08772  -0.0424   1.0000   0.0435
  -9.250  -0.4154   0.09046   0.08354  -0.0441   1.0000   0.0431
  -9.000  -0.4201   0.08607   0.07925  -0.0459   1.0000   0.0426
  -8.750  -0.4273   0.08155   0.07483  -0.0480   1.0000   0.0421
  -8.500  -0.4395   0.07680   0.07019  -0.0502   1.0000   0.0415
  -8.250  -0.4580   0.07279   0.06628  -0.0512   1.0000   0.0410
  -8.000  -0.4741   0.06894   0.06247  -0.0517   1.0000   0.0405
  -7.750  -0.4901   0.06524   0.05874  -0.0513   1.0000   0.0402
  -7.500  -0.5033   0.06172   0.05513  -0.0504   1.0000   0.0399
  -7.250  -0.5127   0.05826   0.05153  -0.0493   1.0000   0.0396
  -7.000  -0.5179   0.05478   0.04783  -0.0481   1.0000   0.0396
  -6.750  -0.5186   0.05134   0.04410  -0.0470   1.0000   0.0397
  -6.500  -0.5150   0.04793   0.04035  -0.0460   1.0000   0.0402
  -6.250  -0.5073   0.04463   0.03666  -0.0451   1.0000   0.0409
  -6.000  -0.4959   0.04150   0.03307  -0.0442   1.0000   0.0418
  -5.750  -0.4811   0.03846   0.02947  -0.0434   1.0000   0.0441
  -5.500  -0.4641   0.03590   0.02645  -0.0425   1.0000   0.0472
  -5.250  -0.4470   0.03440   0.02478  -0.0418   1.0000   0.0516
  -5.000  -0.4183   0.03242   0.02238  -0.0427   0.9964   0.0606
  -4.750  -0.3870   0.03096   0.02068  -0.0443   0.9913   0.0748
  -4.500  -0.3548   0.02932   0.01870  -0.0452   0.9866   0.0861
  -4.250  -0.3231   0.02806   0.01725  -0.0460   0.9821   0.0982
  -4.000  -0.2939   0.02698   0.01613  -0.0465   0.9767   0.1096
  -3.750  -0.2622   0.02606   0.01512  -0.0475   0.9718   0.1222
  -3.500  -0.2322   0.02528   0.01429  -0.0485   0.9662   0.1395
  -3.250  -0.2011   0.02447   0.01351  -0.0498   0.9605   0.1641
  -3.000  -0.1676   0.02326   0.01274  -0.0520   0.9561   0.2407
  -2.750  -0.1481   0.02197   0.01288  -0.0509   0.9496   0.5012
  -2.500  -0.1233   0.02214   0.01327  -0.0492   0.9436   0.6387
  -2.250  -0.1027   0.02235   0.01340  -0.0471   0.9362   0.7056
  -2.000  -0.0832   0.02256   0.01367  -0.0440   0.9296   0.7697
  -1.750  -0.0705   0.02263   0.01380  -0.0394   0.9219   0.8287
  -1.500  -0.0465   0.02262   0.01375  -0.0372   0.9158   0.8828
  -1.250  -0.0041   0.02265   0.01358  -0.0395   0.9104   0.9179
  -1.000   0.0431   0.02267   0.01338  -0.0437   0.9034   0.9398
  -0.750   0.1001   0.02269   0.01315  -0.0498   0.8981   0.9583
  -0.500   0.1472   0.02269   0.01297  -0.0544   0.8895   0.9834
  -0.250   0.1899   0.02271   0.01282  -0.0581   0.8828   1.0000
   0.000   0.2123   0.02279   0.01276  -0.0582   0.8728   1.0000
   0.250   0.2380   0.02294   0.01278  -0.0587   0.8639   1.0000
   0.500   0.2717   0.02307   0.01279  -0.0604   0.8567   1.0000
   0.750   0.2965   0.02331   0.01293  -0.0606   0.8470   1.0000
   1.000   0.3333   0.02344   0.01297  -0.0625   0.8407   1.0000
   1.250   0.3568   0.02373   0.01320  -0.0623   0.8301   1.0000
   1.500   0.3881   0.02393   0.01336  -0.0633   0.8220   1.0000
   1.750   0.4185   0.02413   0.01353  -0.0640   0.8129   1.0000
   2.000   0.4454   0.02434   0.01372  -0.0640   0.8015   1.0000
   2.250   0.4765   0.02435   0.01373  -0.0643   0.7894   1.0000
   2.500   0.5089   0.02425   0.01366  -0.0646   0.7767   1.0000
   2.750   0.5415   0.02412   0.01353  -0.0648   0.7640   1.0000
   3.000   0.5737   0.02401   0.01346  -0.0650   0.7522   1.0000
   3.250   0.6006   0.02407   0.01360  -0.0646   0.7387   1.0000
   3.500   0.6283   0.02406   0.01366  -0.0641   0.7246   1.0000
   3.750   0.6563   0.02402   0.01368  -0.0636   0.7100   1.0000
   4.000   0.6847   0.02393   0.01367  -0.0631   0.6947   1.0000
   4.250   0.7134   0.02380   0.01366  -0.0625   0.6788   1.0000
   4.500   0.7365   0.02389   0.01386  -0.0613   0.6593   1.0000
   4.750   0.7624   0.02382   0.01387  -0.0603   0.6389   1.0000
   5.000   0.7879   0.02372   0.01388  -0.0591   0.6160   1.0000
   5.250   0.8136   0.02358   0.01380  -0.0578   0.5900   1.0000
   5.500   0.8367   0.02360   0.01387  -0.0564   0.5599   1.0000
   5.750   0.8595   0.02370   0.01400  -0.0549   0.5268   1.0000
   6.000   0.8832   0.02385   0.01408  -0.0535   0.4927   1.0000
   6.250   0.9057   0.02421   0.01432  -0.0521   0.4583   1.0000
   6.500   0.9257   0.02481   0.01484  -0.0506   0.4246   1.0000
   6.750   0.9443   0.02555   0.01556  -0.0491   0.3921   1.0000
   7.000   0.9619   0.02637   0.01633  -0.0476   0.3615   1.0000
   7.250   0.9794   0.02724   0.01716  -0.0461   0.3346   1.0000
   7.500   0.9967   0.02821   0.01805  -0.0447   0.3110   1.0000
   7.750   1.0150   0.02926   0.01913  -0.0435   0.2896   1.0000
   8.000   1.0345   0.03036   0.02023  -0.0424   0.2709   1.0000
   8.250   1.0543   0.03148   0.02141  -0.0415   0.2535   1.0000
   8.500   1.0748   0.03263   0.02270  -0.0406   0.2378   1.0000
   8.750   1.0953   0.03382   0.02403  -0.0398   0.2238   1.0000
   9.250   1.1118   0.03604   0.02651  -0.0356   0.1885   1.0000
   9.500   1.1098   0.03721   0.02765  -0.0326   0.1703   1.0000
   9.750   1.1087   0.03865   0.02915  -0.0301   0.1508   1.0000
  10.000   1.1104   0.04031   0.03089  -0.0282   0.1328   1.0000
  10.250   1.1116   0.04227   0.03289  -0.0266   0.1162   1.0000
  10.500   1.1120   0.04458   0.03527  -0.0251   0.0981   1.0000
  10.750   1.1112   0.04722   0.03796  -0.0239   0.0818   1.0000
  11.000   1.1103   0.05008   0.04085  -0.0228   0.0708   1.0000
  11.250   1.1082   0.05308   0.04380  -0.0220   0.0643   1.0000
  11.500   1.1100   0.05605   0.04699  -0.0212   0.0580   1.0000
  11.750   1.1078   0.05922   0.05024  -0.0209   0.0542   1.0000
  12.000   1.1082   0.06252   0.05374  -0.0206   0.0505   1.0000
  12.250   1.1075   0.06598   0.05740  -0.0206   0.0476   1.0000
  12.500   1.1056   0.06960   0.06117  -0.0208   0.0457   1.0000
  12.750   1.1034   0.07335   0.06503  -0.0212   0.0443   1.0000
  13.000   1.1018   0.07726   0.06904  -0.0216   0.0432   1.0000
  13.250   1.0971   0.08196   0.07407  -0.0225   0.0423   1.0000
  13.500   1.0883   0.08740   0.07981  -0.0242   0.0416   1.0000
  13.750   1.0768   0.09346   0.08614  -0.0266   0.0412   1.0000
  14.000   1.0622   0.10040   0.09334  -0.0300   0.0409   1.0000
  14.250   1.0450   0.10833   0.10151  -0.0342   0.0410   1.0000
  14.500   1.0245   0.11762   0.11101  -0.0396   0.0413   1.0000
  14.750   1.0021   0.12815   0.12170  -0.0459   0.0419   1.0000
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