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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 50,000
Max Cl/Cd: 33.91 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2512-il-50000.txt
Download as CSV file: xf-hq2512-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/12 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3704   0.11571   0.10874  -0.0261   1.0000   0.2554
  -9.750  -0.3818   0.11449   0.10762  -0.0267   1.0000   0.2664
  -9.500  -0.3725   0.11087   0.10403  -0.0258   1.0000   0.2806
  -9.250  -0.3673   0.10775   0.10097  -0.0250   1.0000   0.2951
  -9.000  -0.3658   0.10506   0.09835  -0.0242   1.0000   0.3100
  -8.750  -0.3616   0.10213   0.09548  -0.0232   1.0000   0.3245
  -8.500  -0.3599   0.09933   0.09275  -0.0220   1.0000   0.3392
  -8.250  -0.3540   0.09620   0.08968  -0.0207   1.0000   0.3533
  -8.000  -0.3627   0.09447   0.08807  -0.0189   1.0000   0.3690
  -7.750  -0.3353   0.08987   0.08343  -0.0172   1.0000   0.3923
  -7.500  -0.3345   0.08733   0.08095  -0.0155   1.0000   0.4064
  -6.750  -0.5297   0.06858   0.06284  -0.0348   1.0000   0.1814
  -6.500  -0.5464   0.06052   0.05428  -0.0388   1.0000   0.1476
  -6.250  -0.5508   0.05465   0.04767  -0.0403   1.0000   0.1352
  -6.000  -0.5421   0.05071   0.04345  -0.0397   1.0000   0.1346
  -5.750  -0.5303   0.04685   0.03924  -0.0392   1.0000   0.1337
  -5.500  -0.5153   0.04311   0.03500  -0.0388   1.0000   0.1329
  -5.250  -0.4980   0.03991   0.03113  -0.0386   1.0000   0.1365
  -5.000  -0.4795   0.03748   0.02863  -0.0378   1.0000   0.1433
  -4.750  -0.4572   0.03508   0.02551  -0.0374   1.0000   0.1503
  -4.500  -0.4362   0.03310   0.02349  -0.0366   1.0000   0.1601
  -4.250  -0.4138   0.03131   0.02146  -0.0359   1.0000   0.1703
  -4.000  -0.3916   0.02986   0.01982  -0.0351   1.0000   0.1835
  -3.750  -0.3692   0.02853   0.01833  -0.0340   1.0000   0.1966
  -3.500  -0.3483   0.02745   0.01731  -0.0330   1.0000   0.2182
  -3.250  -0.3268   0.02628   0.01625  -0.0318   1.0000   0.2443
  -3.000  -0.3054   0.02492   0.01526  -0.0309   1.0000   0.2984
  -2.750  -0.2968   0.02311   0.01569  -0.0258   1.0000   0.5919
  -2.500  -0.3019   0.02379   0.01661  -0.0163   1.0000   0.7291
  -2.250  -0.3030   0.02403   0.01684  -0.0087   1.0000   0.7959
  -2.000  -0.3024   0.02396   0.01672  -0.0017   1.0000   0.8517
  -1.750  -0.1392   0.02611   0.01811  -0.0204   1.0000   1.0000
  -1.500  -0.1491   0.02550   0.01743  -0.0171   1.0000   1.0000
  -1.250  -0.1579   0.02487   0.01672  -0.0138   1.0000   1.0000
  -1.000  -0.1603   0.02439   0.01610  -0.0116   1.0000   1.0000
  -0.750  -0.1497   0.02427   0.01578  -0.0112   1.0000   1.0000
  -0.500  -0.1320   0.02442   0.01571  -0.0119   1.0000   1.0000
  -0.250  -0.1115   0.02474   0.01579  -0.0129   1.0000   1.0000
   0.000  -0.0900   0.02518   0.01601  -0.0139   1.0000   1.0000
   0.250  -0.0683   0.02570   0.01634  -0.0148   1.0000   1.0000
   0.500  -0.0470   0.02630   0.01675  -0.0157   1.0000   1.0000
   0.750  -0.0083   0.02750   0.01774  -0.0198   0.9922   1.0000
   1.000   0.0371   0.02891   0.01898  -0.0249   0.9797   1.0000
   1.250   0.0800   0.03025   0.02015  -0.0295   0.9670   1.0000
   1.500   0.1217   0.03153   0.02131  -0.0337   0.9536   1.0000
   1.750   0.1618   0.03273   0.02241  -0.0374   0.9394   1.0000
   2.000   0.1995   0.03382   0.02343  -0.0406   0.9240   1.0000
   2.250   0.2362   0.03484   0.02440  -0.0434   0.9068   1.0000
   2.500   0.2766   0.03584   0.02537  -0.0465   0.8880   1.0000
   2.750   0.3233   0.03683   0.02635  -0.0503   0.8694   1.0000
   3.000   0.3579   0.03764   0.02717  -0.0521   0.8504   1.0000
   3.250   0.3919   0.03841   0.02795  -0.0537   0.8313   1.0000
   3.500   0.4331   0.03908   0.02868  -0.0561   0.8127   1.0000
   3.750   0.4760   0.03960   0.02927  -0.0583   0.7942   1.0000
   4.000   0.5028   0.04020   0.02993  -0.0584   0.7734   1.0000
   4.250   0.5473   0.04036   0.03022  -0.0602   0.7541   1.0000
   4.500   0.5828   0.04056   0.03053  -0.0608   0.7334   1.0000
   5.000   0.6820   0.03917   0.02950  -0.0635   0.6944   1.0000
   5.250   0.7095   0.03908   0.02953  -0.0623   0.6705   1.0000
   5.500   0.7702   0.03696   0.02767  -0.0633   0.6521   1.0000
   5.750   0.8052   0.03610   0.02696  -0.0621   0.6282   1.0000
   6.000   0.8677   0.03334   0.02441  -0.0627   0.6075   1.0000
   6.250   0.9038   0.03227   0.02345  -0.0614   0.5803   1.0000
   6.500   0.9413   0.03123   0.02245  -0.0603   0.5520   1.0000
   6.750   0.9763   0.03051   0.02176  -0.0592   0.5226   1.0000
   7.000   1.0072   0.03033   0.02151  -0.0580   0.4931   1.0000
   7.250   1.0346   0.03059   0.02170  -0.0568   0.4640   1.0000
   7.500   1.0587   0.03122   0.02227  -0.0554   0.4358   1.0000
   7.750   1.0804   0.03217   0.02320  -0.0539   0.4090   1.0000
   8.000   1.1020   0.03324   0.02427  -0.0526   0.3834   1.0000
   8.250   1.1266   0.03434   0.02527  -0.0516   0.3592   1.0000
   8.500   1.1436   0.03582   0.02684  -0.0500   0.3370   1.0000
   8.750   1.1675   0.03729   0.02824  -0.0491   0.3161   1.0000
   9.000   1.1816   0.03911   0.03022  -0.0473   0.2970   1.0000
   9.250   1.1993   0.04105   0.03232  -0.0459   0.2796   1.0000
   9.500   1.2172   0.04303   0.03438  -0.0446   0.2631   1.0000
   9.750   1.2337   0.04506   0.03650  -0.0432   0.2474   1.0000
  10.000   1.2424   0.04761   0.03932  -0.0411   0.2349   1.0000
  10.250   1.2481   0.05016   0.04213  -0.0388   0.2228   1.0000
  10.500   1.2548   0.05277   0.04495  -0.0367   0.2116   1.0000
  10.750   1.2659   0.05537   0.04768  -0.0350   0.2001   1.0000
  11.000   1.2750   0.05756   0.04997  -0.0331   0.1871   1.0000
  11.250   1.2507   0.06151   0.05438  -0.0290   0.1835   1.0000
  11.500   1.2547   0.06386   0.05681  -0.0269   0.1717   1.0000
  11.750   1.2251   0.06802   0.06127  -0.0232   0.1707   1.0000
  12.000   1.1929   0.07291   0.06636  -0.0207   0.1710   1.0000
  12.250   1.1594   0.07885   0.07246  -0.0199   0.1723   1.0000
  12.500   1.1254   0.08582   0.07953  -0.0206   0.1737   1.0000
  12.750   1.2200   0.07536   0.06861  -0.0150   0.1202   1.0000
  13.000   1.1937   0.08068   0.07414  -0.0144   0.1199   1.0000
  13.250   0.8028   0.16200   0.15456  -0.0737   0.3450   1.0000
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