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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 500,000
Max Cl/Cd: 84.36 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2511-il-500000-n5.txt
Download as CSV file: xf-hq2511-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6522   0.04395   0.04141  -0.0683   1.0000   0.0059
 -10.250  -0.6867   0.04006   0.03738  -0.0667   1.0000   0.0058
 -10.000  -0.6850   0.03380   0.03061  -0.0717   0.9868   0.0059
  -9.750  -0.6696   0.02939   0.02572  -0.0750   0.9789   0.0059
  -9.500  -0.6472   0.02651   0.02246  -0.0772   0.9724   0.0060
  -9.250  -0.6240   0.02420   0.01982  -0.0786   0.9653   0.0061
  -9.000  -0.5978   0.02254   0.01789  -0.0798   0.9586   0.0062
  -8.750  -0.5737   0.02108   0.01617  -0.0802   0.9505   0.0063
  -8.500  -0.5484   0.01987   0.01474  -0.0806   0.9428   0.0065
  -8.250  -0.5256   0.01880   0.01348  -0.0803   0.9330   0.0065
  -8.000  -0.5022   0.01777   0.01228  -0.0800   0.9239   0.0065
  -7.750  -0.4789   0.01680   0.01114  -0.0796   0.9144   0.0066
  -7.500  -0.4553   0.01596   0.01017  -0.0791   0.9052   0.0066
  -7.250  -0.4312   0.01521   0.00928  -0.0787   0.8967   0.0066
  -7.000  -0.4068   0.01454   0.00848  -0.0783   0.8880   0.0066
  -6.750  -0.3820   0.01393   0.00776  -0.0779   0.8803   0.0067
  -6.500  -0.3570   0.01332   0.00704  -0.0775   0.8728   0.0067
  -6.250  -0.3317   0.01276   0.00638  -0.0772   0.8662   0.0068
  -6.000  -0.3059   0.01232   0.00582  -0.0769   0.8593   0.0069
  -5.750  -0.2799   0.01188   0.00528  -0.0767   0.8530   0.0072
  -5.500  -0.2534   0.01152   0.00485  -0.0765   0.8462   0.0073
  -5.000  -0.2001   0.01089   0.00406  -0.0761   0.8336   0.0081
  -4.750  -0.1733   0.01063   0.00372  -0.0759   0.8266   0.0086
  -4.500  -0.1464   0.01036   0.00341  -0.0758   0.8193   0.0102
  -4.250  -0.1197   0.01006   0.00313  -0.0756   0.8123   0.0193
  -4.000  -0.0925   0.00983   0.00291  -0.0756   0.8060   0.0286
  -3.750  -0.0650   0.00966   0.00274  -0.0755   0.7997   0.0359
  -3.500  -0.0376   0.00949   0.00258  -0.0755   0.7937   0.0456
  -3.250  -0.0101   0.00931   0.00242  -0.0754   0.7868   0.0562
  -3.000   0.0173   0.00916   0.00226  -0.0754   0.7805   0.0678
  -2.750   0.0450   0.00900   0.00213  -0.0754   0.7733   0.0806
  -2.500   0.0723   0.00881   0.00198  -0.0753   0.7668   0.1039
  -2.250   0.0987   0.00832   0.00181  -0.0754   0.7596   0.2009
  -2.000   0.1244   0.00771   0.00163  -0.0755   0.7528   0.3330
  -1.750   0.1511   0.00733   0.00155  -0.0755   0.7467   0.4370
  -1.500   0.1779   0.00708   0.00150  -0.0754   0.7397   0.5088
  -1.250   0.2051   0.00697   0.00149  -0.0752   0.7316   0.5565
  -1.000   0.2324   0.00693   0.00150  -0.0750   0.7233   0.5928
  -0.750   0.2600   0.00690   0.00152  -0.0749   0.7154   0.6237
  -0.500   0.2873   0.00691   0.00155  -0.0747   0.7081   0.6521
  -0.250   0.3152   0.00691   0.00156  -0.0746   0.6999   0.6682
   0.000   0.3429   0.00695   0.00156  -0.0745   0.6906   0.6783
   0.250   0.3704   0.00699   0.00156  -0.0743   0.6792   0.6867
   0.500   0.3981   0.00702   0.00157  -0.0743   0.6685   0.6950
   0.750   0.4258   0.00706   0.00160  -0.0742   0.6589   0.7036
   1.000   0.4532   0.00711   0.00162  -0.0740   0.6469   0.7110
   1.250   0.4807   0.00716   0.00165  -0.0739   0.6355   0.7183
   1.500   0.5083   0.00721   0.00170  -0.0738   0.6242   0.7244
   1.750   0.5355   0.00728   0.00175  -0.0736   0.6097   0.7311
   2.000   0.5620   0.00739   0.00179  -0.0733   0.5878   0.7375
   2.250   0.5872   0.00757   0.00186  -0.0728   0.5508   0.7441
   2.750   0.6356   0.00815   0.00211  -0.0715   0.4681   0.7584
   3.000   0.6608   0.00840   0.00227  -0.0711   0.4435   0.7665
   3.250   0.6861   0.00861   0.00243  -0.0707   0.4211   0.7751
   3.500   0.7112   0.00883   0.00260  -0.0702   0.3965   0.7858
   3.750   0.7359   0.00905   0.00279  -0.0697   0.3679   0.7992
   4.500   0.8061   0.00994   0.00347  -0.0675   0.2801   0.8456
   4.750   0.8296   0.01013   0.00369  -0.0667   0.2647   0.8675
   5.000   0.8521   0.01026   0.00390  -0.0656   0.2498   0.9081
   5.250   0.8858   0.01050   0.00415  -0.0671   0.2311   1.0000
   5.500   0.9100   0.01087   0.00442  -0.0666   0.2096   1.0000
   5.750   0.9333   0.01130   0.00473  -0.0661   0.1837   1.0000
   6.250   0.9788   0.01224   0.00542  -0.0648   0.1349   1.0000
   6.500   1.0020   0.01266   0.00578  -0.0642   0.1198   1.0000
   6.750   1.0249   0.01308   0.00614  -0.0635   0.1063   1.0000
   7.000   1.0480   0.01348   0.00651  -0.0629   0.0957   1.0000
   7.250   1.0703   0.01392   0.00692  -0.0622   0.0830   1.0000
   7.500   1.0904   0.01455   0.00742  -0.0611   0.0610   1.0000
   7.750   1.1038   0.01574   0.00831  -0.0592   0.0219   1.0000
   8.000   1.1239   0.01633   0.00891  -0.0581   0.0171   1.0000
   8.250   1.1434   0.01695   0.00957  -0.0569   0.0145   1.0000
   8.500   1.1638   0.01745   0.01014  -0.0559   0.0136   1.0000
   8.750   1.1832   0.01801   0.01076  -0.0547   0.0126   1.0000
   9.000   1.2013   0.01863   0.01144  -0.0533   0.0116   1.0000
   9.250   1.2161   0.01941   0.01227  -0.0515   0.0106   1.0000
   9.500   1.2311   0.02005   0.01299  -0.0496   0.0102   1.0000
   9.750   1.2455   0.02071   0.01374  -0.0477   0.0098   1.0000
  10.000   1.2587   0.02146   0.01456  -0.0457   0.0094   1.0000
  10.250   1.2710   0.02226   0.01544  -0.0437   0.0091   1.0000
  10.500   1.2829   0.02311   0.01636  -0.0417   0.0087   1.0000
  10.750   1.2934   0.02406   0.01740  -0.0397   0.0084   1.0000
  11.000   1.3032   0.02509   0.01850  -0.0378   0.0081   1.0000
  11.250   1.3102   0.02634   0.01982  -0.0357   0.0077   1.0000
  11.500   1.3123   0.02801   0.02159  -0.0334   0.0075   1.0000
  11.750   1.3210   0.02923   0.02292  -0.0318   0.0073   1.0000
  12.000   1.3292   0.03054   0.02433  -0.0303   0.0071   1.0000
  12.250   1.3360   0.03202   0.02592  -0.0289   0.0068   1.0000
  12.500   1.3398   0.03381   0.02782  -0.0274   0.0067   1.0000
  12.750   1.3434   0.03570   0.02982  -0.0261   0.0065   1.0000
  13.000   1.3472   0.03764   0.03187  -0.0251   0.0064   1.0000
  13.250   1.3489   0.03987   0.03421  -0.0242   0.0062   1.0000
  13.500   1.3494   0.04232   0.03677  -0.0235   0.0061   1.0000
  13.750   1.3501   0.04484   0.03940  -0.0230   0.0059   1.0000
  14.000   1.3498   0.04759   0.04227  -0.0227   0.0058   1.0000
  14.250   1.3486   0.05056   0.04535  -0.0227   0.0057   1.0000
  14.500   1.3458   0.05386   0.04878  -0.0230   0.0056   1.0000
  14.750   1.3410   0.05759   0.05264  -0.0236   0.0056   1.0000
  15.000   1.3359   0.06156   0.05673  -0.0245   0.0055   1.0000
  15.250   1.3291   0.06599   0.06128  -0.0258   0.0054   1.0000
  15.500   1.3211   0.07084   0.06626  -0.0276   0.0053   1.0000
  15.750   1.3116   0.07615   0.07171  -0.0296   0.0052   1.0000
  16.000   1.3012   0.08184   0.07753  -0.0321   0.0052   1.0000
  16.250   1.2872   0.08833   0.08416  -0.0350   0.0051   1.0000
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