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HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il)
Reynolds number: 500,000
Max Cl/Cd: 82.23 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1511-il-500000.txt
Download as CSV file: xf-hq1511-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/11 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4572   0.09740   0.09524  -0.0252   1.0000   0.0170
 -11.500  -0.6682   0.06539   0.06297  -0.0432   1.0000   0.0121
 -11.250  -0.6950   0.05608   0.05352  -0.0513   1.0000   0.0120
 -11.000  -0.7166   0.05006   0.04735  -0.0556   1.0000   0.0119
 -10.750  -0.7424   0.04485   0.04195  -0.0578   1.0000   0.0118
 -10.500  -0.7658   0.04122   0.03812  -0.0566   1.0000   0.0117
 -10.250  -0.7856   0.03737   0.03399  -0.0541   1.0000   0.0116
 -10.000  -0.7964   0.03334   0.02958  -0.0517   1.0000   0.0115
  -9.750  -0.7989   0.02983   0.02568  -0.0494   1.0000   0.0114
  -9.500  -0.7938   0.02721   0.02274  -0.0472   1.0000   0.0114
  -9.250  -0.7852   0.02508   0.02032  -0.0450   1.0000   0.0115
  -9.000  -0.7748   0.02338   0.01839  -0.0427   1.0000   0.0116
  -8.750  -0.7651   0.02197   0.01680  -0.0401   1.0000   0.0117
  -8.500  -0.7536   0.02065   0.01532  -0.0378   0.9996   0.0118
  -8.250  -0.7205   0.01916   0.01362  -0.0397   0.9962   0.0119
  -8.000  -0.6868   0.01802   0.01232  -0.0415   0.9925   0.0123
  -7.750  -0.6536   0.01699   0.01115  -0.0432   0.9881   0.0126
  -7.500  -0.6207   0.01551   0.00956  -0.0451   0.9846   0.0131
  -7.250  -0.5873   0.01458   0.00856  -0.0467   0.9805   0.0135
  -7.000  -0.5535   0.01382   0.00774  -0.0483   0.9757   0.0141
  -6.750  -0.5185   0.01315   0.00699  -0.0501   0.9716   0.0150
  -6.500  -0.4861   0.01259   0.00635  -0.0513   0.9651   0.0164
  -6.250  -0.4546   0.01191   0.00566  -0.0523   0.9585   0.0203
  -6.000  -0.4259   0.01141   0.00519  -0.0526   0.9497   0.0302
  -5.750  -0.3964   0.01119   0.00493  -0.0529   0.9419   0.0367
  -5.500  -0.3709   0.01093   0.00469  -0.0525   0.9311   0.0429
  -5.250  -0.3445   0.01074   0.00443  -0.0522   0.9216   0.0469
  -5.000  -0.3189   0.01044   0.00412  -0.0517   0.9127   0.0532
  -4.750  -0.2932   0.01023   0.00387  -0.0512   0.9024   0.0602
  -4.500  -0.2674   0.01000   0.00363  -0.0508   0.8929   0.0696
  -4.250  -0.2419   0.00971   0.00334  -0.0503   0.8838   0.0822
  -4.000  -0.2162   0.00940   0.00307  -0.0499   0.8746   0.1023
  -3.750  -0.1920   0.00885   0.00279  -0.0495   0.8662   0.1754
  -3.500  -0.1676   0.00834   0.00256  -0.0491   0.8562   0.2533
  -3.250  -0.1442   0.00765   0.00232  -0.0486   0.8470   0.3772
  -3.000  -0.1197   0.00723   0.00217  -0.0481   0.8388   0.4737
  -2.750  -0.0941   0.00696   0.00213  -0.0476   0.8305   0.5427
  -2.500  -0.0673   0.00689   0.00209  -0.0473   0.8235   0.5826
  -2.250  -0.0401   0.00683   0.00207  -0.0470   0.8154   0.6127
  -2.000  -0.0129   0.00681   0.00205  -0.0467   0.8088   0.6379
  -1.750   0.0147   0.00680   0.00204  -0.0465   0.8008   0.6565
  -1.500   0.0423   0.00682   0.00202  -0.0463   0.7943   0.6738
  -1.250   0.0698   0.00681   0.00203  -0.0460   0.7872   0.6903
  -1.000   0.0972   0.00682   0.00203  -0.0457   0.7804   0.7056
  -0.750   0.1250   0.00683   0.00202  -0.0456   0.7727   0.7160
  -0.500   0.1525   0.00682   0.00199  -0.0454   0.7648   0.7247
  -0.250   0.1802   0.00682   0.00198  -0.0452   0.7556   0.7349
   0.000   0.2077   0.00684   0.00197  -0.0449   0.7479   0.7445
   0.250   0.2354   0.00682   0.00197  -0.0448   0.7393   0.7522
   0.500   0.2631   0.00684   0.00197  -0.0447   0.7311   0.7605
   0.750   0.2907   0.00684   0.00197  -0.0445   0.7221   0.7681
   1.000   0.3184   0.00685   0.00199  -0.0443   0.7127   0.7762
   1.250   0.3458   0.00687   0.00200  -0.0441   0.7041   0.7838
   1.500   0.3735   0.00689   0.00203  -0.0440   0.6942   0.7929
   1.750   0.4007   0.00689   0.00207  -0.0437   0.6847   0.8007
   2.000   0.4281   0.00692   0.00209  -0.0436   0.6746   0.8093
   2.250   0.4552   0.00692   0.00214  -0.0433   0.6628   0.8184
   2.500   0.4822   0.00693   0.00218  -0.0430   0.6502   0.8279
   2.750   0.5089   0.00696   0.00223  -0.0427   0.6350   0.8385
   3.000   0.5347   0.00700   0.00226  -0.0421   0.6130   0.8493
   3.250   0.5597   0.00708   0.00230  -0.0414   0.5807   0.8617
   3.500   0.5831   0.00722   0.00237  -0.0404   0.5383   0.8781
   3.750   0.6051   0.00744   0.00248  -0.0391   0.4922   0.8994
   4.000   0.6277   0.00771   0.00264  -0.0380   0.4508   0.9290
   4.250   0.6611   0.00804   0.00285  -0.0394   0.4065   0.9633
   4.500   0.6974   0.00853   0.00310  -0.0417   0.3408   1.0000
   4.750   0.7208   0.00899   0.00335  -0.0412   0.3045   1.0000
   5.000   0.7452   0.00937   0.00361  -0.0408   0.2813   1.0000
   5.250   0.7698   0.00972   0.00388  -0.0404   0.2608   1.0000
   5.500   0.7948   0.01004   0.00413  -0.0400   0.2423   1.0000
   5.750   0.8198   0.01034   0.00439  -0.0397   0.2266   1.0000
   6.000   0.8447   0.01066   0.00465  -0.0393   0.2101   1.0000
   6.250   0.8692   0.01100   0.00494  -0.0389   0.1896   1.0000
   6.500   0.8928   0.01143   0.00521  -0.0384   0.1497   1.0000
   6.750   0.9142   0.01207   0.00566  -0.0376   0.1160   1.0000
   7.000   0.9359   0.01269   0.00614  -0.0368   0.0940   1.0000
   7.250   0.9583   0.01322   0.00662  -0.0361   0.0763   1.0000
   7.500   0.9796   0.01386   0.00715  -0.0352   0.0583   1.0000
   7.750   1.0003   0.01455   0.00778  -0.0342   0.0447   1.0000
   8.000   1.0198   0.01536   0.00854  -0.0330   0.0362   1.0000
   8.250   1.0420   0.01584   0.00908  -0.0322   0.0326   1.0000
   8.500   1.0607   0.01665   0.00989  -0.0309   0.0290   1.0000
   8.750   1.0791   0.01744   0.01076  -0.0296   0.0272   1.0000
   9.000   1.0987   0.01808   0.01148  -0.0284   0.0256   1.0000
   9.250   1.1171   0.01879   0.01223  -0.0272   0.0241   1.0000
   9.500   1.1328   0.01968   0.01315  -0.0256   0.0226   1.0000
   9.750   1.1414   0.02112   0.01470  -0.0230   0.0212   1.0000
  10.000   1.1570   0.02184   0.01551  -0.0214   0.0206   1.0000
  10.250   1.1695   0.02268   0.01644  -0.0192   0.0199   1.0000
  10.500   1.1813   0.02355   0.01739  -0.0171   0.0191   1.0000
  10.750   1.1923   0.02448   0.01839  -0.0150   0.0183   1.0000
  11.000   1.2030   0.02540   0.01935  -0.0132   0.0175   1.0000
  11.250   1.2093   0.02682   0.02083  -0.0109   0.0169   1.0000
  11.500   1.2095   0.02922   0.02336  -0.0084   0.0161   1.0000
  11.750   1.2191   0.03043   0.02471  -0.0068   0.0158   1.0000
  12.000   1.2277   0.03173   0.02614  -0.0053   0.0154   1.0000
  12.250   1.2345   0.03331   0.02785  -0.0038   0.0149   1.0000
  12.500   1.2411   0.03482   0.02947  -0.0025   0.0144   1.0000
  12.750   1.2457   0.03665   0.03142  -0.0013   0.0140   1.0000
  13.000   1.2496   0.03851   0.03339  -0.0003   0.0136   1.0000
  13.250   1.2530   0.04046   0.03543   0.0005   0.0132   1.0000
  13.500   1.2555   0.04254   0.03758   0.0010   0.0128   1.0000
  13.750   1.2539   0.04531   0.04043   0.0015   0.0125   1.0000
  14.250   1.2331   0.05365   0.04917   0.0018   0.0119   1.0000
  14.500   1.2294   0.05687   0.05255   0.0011   0.0118   1.0000
  14.750   1.2211   0.06103   0.05689   0.0000   0.0117   1.0000
  15.000   1.2116   0.06558   0.06163  -0.0016   0.0115   1.0000
  15.250   1.2000   0.07080   0.06704  -0.0038   0.0114   1.0000
  15.500   1.1877   0.07647   0.07289  -0.0066   0.0113   1.0000
  15.750   1.1736   0.08289   0.07948  -0.0101   0.0112   1.0000
  16.000   1.1558   0.09036   0.08714  -0.0143   0.0112   1.0000
  16.250   1.1380   0.09827   0.09522  -0.0191   0.0112   1.0000
  16.500   1.1148   0.10779   0.10491  -0.0249   0.0113   1.0000
  16.750   1.0920   0.11776   0.11505  -0.0311   0.0114   1.0000
  17.000   1.0677   0.12861   0.12606  -0.0380   0.0114   1.0000
  17.250   1.0357   0.14191   0.13952  -0.0463   0.0117   1.0000
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