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HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9 AIRFOIL (hq259-il)
Reynolds number: 100,000
Max Cl/Cd: 58.58 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq259-il-100000.txt
Download as CSV file: xf-hq259-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3221   0.09298   0.08845  -0.0321   1.0000   0.0851
  -8.750  -0.3312   0.08985   0.08540  -0.0345   1.0000   0.0879
  -8.500  -0.3491   0.08711   0.08277  -0.0380   1.0000   0.0890
  -8.250  -0.3658   0.08431   0.08008  -0.0403   1.0000   0.0893
  -8.000  -0.3296   0.07856   0.07428  -0.0343   1.0000   0.0950
  -7.750  -0.3345   0.07541   0.07121  -0.0344   1.0000   0.0983
  -7.500  -0.3491   0.07268   0.06858  -0.0348   1.0000   0.1007
  -7.250  -0.3748   0.07064   0.06670  -0.0344   1.0000   0.1017
  -7.000  -0.3982   0.06789   0.06404  -0.0363   1.0000   0.1022
  -6.750  -0.4231   0.06531   0.06142  -0.0381   1.0000   0.1027
  -6.500  -0.4115   0.06114   0.05740  -0.0327   1.0000   0.1056
  -6.250  -0.4132   0.05867   0.05497  -0.0301   1.0000   0.1091
  -6.000  -0.4484   0.06392   0.05976  -0.0373   1.0000   0.1090
  -5.750  -0.4520   0.06025   0.05579  -0.0412   1.0000   0.1177
  -5.500  -0.4446   0.05743   0.05313  -0.0379   1.0000   0.1216
  -5.250  -0.4385   0.05405   0.04956  -0.0394   1.0000   0.1328
  -5.000  -0.4290   0.05114   0.04649  -0.0397   1.0000   0.1458
  -4.750  -0.4179   0.04827   0.04356  -0.0393   1.0000   0.1599
  -4.500  -0.4057   0.04560   0.04088  -0.0385   1.0000   0.1750
  -4.250  -0.3560   0.03693   0.03069  -0.0433   1.0000   0.0875
  -4.000  -0.3240   0.03112   0.02406  -0.0433   1.0000   0.0581
  -3.750  -0.2983   0.02839   0.02085  -0.0431   1.0000   0.0569
  -3.500  -0.2727   0.02650   0.01842  -0.0426   1.0000   0.0597
  -3.250  -0.2463   0.02448   0.01596  -0.0420   1.0000   0.0604
  -3.000  -0.2208   0.02300   0.01408  -0.0411   1.0000   0.0623
  -2.750  -0.1966   0.02113   0.01224  -0.0406   1.0000   0.0696
  -2.500  -0.1732   0.02008   0.01116  -0.0400   1.0000   0.0856
  -2.250  -0.1498   0.01890   0.01012  -0.0394   1.0000   0.1140
  -2.000  -0.1267   0.01798   0.00940  -0.0390   1.0000   0.1570
  -1.750  -0.1032   0.01556   0.00948  -0.0377   0.9972   0.7018
  -1.500  -0.0809   0.01568   0.00978  -0.0351   0.9897   0.8278
  -1.250  -0.0338   0.01550   0.00965  -0.0379   0.9830   1.0000
  -1.000   0.0076   0.01582   0.00964  -0.0417   0.9750   1.0000
  -0.750   0.0554   0.01630   0.00979  -0.0465   0.9686   1.0000
  -0.500   0.0923   0.01656   0.00983  -0.0492   0.9592   1.0000
  -0.250   0.1331   0.01692   0.00999  -0.0525   0.9511   1.0000
   0.000   0.1757   0.01724   0.01014  -0.0560   0.9431   1.0000
   0.250   0.2113   0.01752   0.01028  -0.0581   0.9335   1.0000
   0.500   0.2535   0.01780   0.01046  -0.0613   0.9257   1.0000
   0.750   0.2924   0.01803   0.01061  -0.0638   0.9165   1.0000
   1.000   0.3276   0.01826   0.01077  -0.0655   0.9063   1.0000
   1.250   0.3706   0.01833   0.01081  -0.0684   0.8963   1.0000
   1.500   0.4268   0.01806   0.01055  -0.0732   0.8874   1.0000
   1.750   0.4670   0.01791   0.01043  -0.0751   0.8752   1.0000
   2.000   0.5034   0.01782   0.01035  -0.0763   0.8634   1.0000
   2.250   0.5397   0.01767   0.01024  -0.0774   0.8519   1.0000
   2.500   0.5760   0.01744   0.01007  -0.0782   0.8402   1.0000
   2.750   0.6110   0.01716   0.00989  -0.0786   0.8277   1.0000
   3.000   0.6436   0.01686   0.00966  -0.0785   0.8138   1.0000
   3.250   0.6744   0.01655   0.00942  -0.0779   0.7986   1.0000
   3.500   0.7047   0.01622   0.00916  -0.0772   0.7825   1.0000
   3.750   0.7350   0.01584   0.00889  -0.0764   0.7656   1.0000
   4.000   0.7608   0.01562   0.00875  -0.0749   0.7439   1.0000
   4.250   0.7882   0.01532   0.00850  -0.0736   0.7208   1.0000
   4.500   0.8139   0.01511   0.00835  -0.0721   0.6933   1.0000
   4.750   0.8385   0.01499   0.00826  -0.0705   0.6601   1.0000
   5.000   0.8622   0.01497   0.00827  -0.0688   0.6195   1.0000
   5.250   0.8845   0.01510   0.00831  -0.0669   0.5691   1.0000
   5.500   0.9049   0.01550   0.00848  -0.0649   0.5092   1.0000
   5.750   0.9238   0.01621   0.00888  -0.0629   0.4484   1.0000
   6.000   0.9422   0.01712   0.00949  -0.0611   0.3943   1.0000
   6.250   0.9610   0.01808   0.01025  -0.0596   0.3478   1.0000
   6.500   0.9802   0.01911   0.01118  -0.0582   0.3088   1.0000
   6.750   0.9996   0.02021   0.01212  -0.0568   0.2746   1.0000
   7.000   1.0175   0.02117   0.01304  -0.0554   0.2397   1.0000
   7.250   1.0325   0.02178   0.01363  -0.0537   0.2006   1.0000
   7.500   1.0473   0.02238   0.01413  -0.0523   0.1480   1.0000
   7.750   1.0509   0.02527   0.01622  -0.0491   0.0570   1.0000
   8.000   1.0606   0.02748   0.01842  -0.0463   0.0435   1.0000
   8.250   1.0695   0.02992   0.02080  -0.0438   0.0383   1.0000
   8.500   1.0877   0.03199   0.02308  -0.0421   0.0355   1.0000
   8.750   1.1086   0.03447   0.02574  -0.0408   0.0334   1.0000
   9.000   1.1306   0.03734   0.02885  -0.0398   0.0321   1.0000
   9.250   1.1506   0.04062   0.03254  -0.0386   0.0314   1.0000
   9.500   1.1646   0.04379   0.03603  -0.0371   0.0304   1.0000
   9.750   1.1741   0.04723   0.03968  -0.0356   0.0289   1.0000
  10.000   1.1775   0.05168   0.04449  -0.0336   0.0282   1.0000
  10.250   1.1734   0.05631   0.04953  -0.0312   0.0279   1.0000
  10.500   1.1644   0.06046   0.05404  -0.0286   0.0277   1.0000
  10.750   1.1545   0.06343   0.05729  -0.0256   0.0279   1.0000
  11.000   1.1399   0.06684   0.06096  -0.0231   0.0279   1.0000
  11.250   1.1274   0.06977   0.06413  -0.0214   0.0281   1.0000
  11.500   1.1101   0.07363   0.06824  -0.0207   0.0282   1.0000
  11.750   1.0926   0.07751   0.07240  -0.0210   0.0288   1.0000
  12.000   1.0699   0.08305   0.07818  -0.0229   0.0290   1.0000
  12.250   1.0038   0.09773   0.09336  -0.0332   0.0337   1.0000
  12.500   0.9785   0.10794   0.10365  -0.0402   0.0354   1.0000
  12.750   0.9605   0.11759   0.11331  -0.0462   0.0367   1.0000
  13.000   0.9503   0.12557   0.12121  -0.0503   0.0377   1.0000
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