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HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 100,000
Max Cl/Cd: 55.77 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3514-il-100000.txt
Download as CSV file: xf-hq3514-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/14 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  -0.4010   0.10151   0.09719  -0.0327   1.0000   0.1416
  -8.750  -0.4394   0.10024   0.09606  -0.0321   1.0000   0.1446
  -8.500  -0.4868   0.09887   0.09484  -0.0316   1.0000   0.1454
  -8.250  -0.4520   0.09586   0.09180  -0.0270   1.0000   0.1504
  -8.000  -0.4629   0.09441   0.09040  -0.0246   1.0000   0.1553
  -7.750  -0.5323   0.08554   0.08151  -0.0459   0.9859   0.1610
  -7.500  -0.4685   0.08714   0.08319  -0.0319   0.9886   0.1724
  -7.250  -0.4578   0.08332   0.07937  -0.0347   0.9835   0.1827
  -7.000  -0.4726   0.07659   0.07263  -0.0447   0.9736   0.1945
  -6.750  -0.5120   0.05084   0.04505  -0.0651   0.9625   0.1025
  -6.500  -0.4884   0.04642   0.04031  -0.0666   0.9588   0.0964
  -6.250  -0.4600   0.04239   0.03569  -0.0692   0.9556   0.0962
  -6.000  -0.4434   0.03973   0.03258  -0.0686   0.9501   0.0968
  -5.750  -0.4160   0.03715   0.02948  -0.0696   0.9459   0.0976
  -5.500  -0.3828   0.03583   0.02752  -0.0711   0.9425   0.1008
  -5.250  -0.3555   0.03330   0.02480  -0.0719   0.9395   0.1036
  -5.000  -0.3346   0.03218   0.02359  -0.0713   0.9347   0.1073
  -4.750  -0.3037   0.03121   0.02239  -0.0721   0.9302   0.1128
  -4.500  -0.2656   0.03002   0.02096  -0.0740   0.9267   0.1175
  -4.250  -0.2445   0.02923   0.02024  -0.0733   0.9212   0.1238
  -4.000  -0.2135   0.02859   0.01944  -0.0739   0.9153   0.1314
  -3.750  -0.1715   0.02773   0.01874  -0.0765   0.9110   0.1434
  -3.500  -0.1529   0.02726   0.01838  -0.0752   0.9028   0.1535
  -3.250  -0.1141   0.02673   0.01795  -0.0771   0.8973   0.1735
  -3.000  -0.0896   0.02626   0.01765  -0.0769   0.8905   0.2010
  -2.750  -0.0655   0.02456   0.01720  -0.0774   0.8853   0.3738
  -2.500  -0.0393   0.02493   0.01831  -0.0755   0.8810   0.6245
  -2.250  -0.0282   0.02561   0.01899  -0.0719   0.8740   0.6628
  -2.000  -0.0049   0.02615   0.01949  -0.0703   0.8683   0.6951
  -1.750   0.0284   0.02661   0.01990  -0.0699   0.8644   0.7260
  -1.500   0.0336   0.02704   0.02032  -0.0658   0.8554   0.7448
  -1.250   0.0652   0.02726   0.02046  -0.0656   0.8503   0.7684
  -1.000   0.0768   0.02758   0.02078  -0.0624   0.8421   0.7858
  -0.750   0.1003   0.02770   0.02089  -0.0607   0.8360   0.8063
  -0.500   0.1181   0.02789   0.02107  -0.0584   0.8292   0.8270
  -0.250   0.1354   0.02799   0.02115  -0.0562   0.8215   0.8472
   0.000   0.1690   0.02781   0.02095  -0.0560   0.8175   0.8661
   0.250   0.1785   0.02798   0.02111  -0.0532   0.8062   0.8811
   0.500   0.2250   0.02755   0.02061  -0.0555   0.8018   0.8953
   0.750   0.2416   0.02756   0.02062  -0.0538   0.7896   0.9117
   1.000   0.2957   0.02693   0.01993  -0.0572   0.7856   0.9261
   1.250   0.3255   0.02704   0.02006  -0.0582   0.7739   0.9437
   1.500   0.3906   0.02638   0.01935  -0.0640   0.7711   0.9553
   1.750   0.4363   0.02649   0.01946  -0.0682   0.7598   0.9734
   2.000   0.5062   0.02555   0.01849  -0.0747   0.7568   0.9845
   2.250   0.5311   0.02562   0.01853  -0.0754   0.7453   1.0000
   2.500   0.5788   0.02491   0.01779  -0.0785   0.7413   1.0000
   2.750   0.6011   0.02507   0.01793  -0.0784   0.7298   1.0000
   3.000   0.6510   0.02424   0.01706  -0.0814   0.7257   1.0000
   3.250   0.6773   0.02433   0.01715  -0.0816   0.7143   1.0000
   3.500   0.7256   0.02350   0.01630  -0.0843   0.7096   1.0000
   3.750   0.7523   0.02354   0.01634  -0.0843   0.6979   1.0000
   4.000   0.8045   0.02233   0.01511  -0.0870   0.6926   1.0000
   4.250   0.8332   0.02203   0.01480  -0.0868   0.6791   1.0000
   4.500   0.8646   0.02159   0.01435  -0.0868   0.6658   1.0000
   4.750   0.8974   0.02110   0.01385  -0.0869   0.6526   1.0000
   5.000   0.9301   0.02064   0.01337  -0.0871   0.6388   1.0000
   5.250   0.9609   0.02030   0.01302  -0.0870   0.6243   1.0000
   5.500   0.9892   0.02008   0.01279  -0.0866   0.6084   1.0000
   5.750   1.0154   0.01994   0.01264  -0.0859   0.5909   1.0000
   6.000   1.0416   0.01982   0.01250  -0.0852   0.5721   1.0000
   6.250   1.0691   0.01970   0.01231  -0.0846   0.5525   1.0000
   6.500   1.0902   0.01985   0.01243  -0.0832   0.5299   1.0000
   6.750   1.1144   0.02000   0.01245  -0.0823   0.5073   1.0000
   7.000   1.1360   0.02037   0.01272  -0.0811   0.4840   1.0000
   7.250   1.1591   0.02086   0.01305  -0.0802   0.4616   1.0000
   7.500   1.1806   0.02151   0.01357  -0.0792   0.4394   1.0000
   7.750   1.1992   0.02222   0.01423  -0.0777   0.4173   1.0000
   8.000   1.2181   0.02293   0.01482  -0.0764   0.3962   1.0000
   8.250   1.2321   0.02364   0.01552  -0.0743   0.3755   1.0000
   8.500   1.2459   0.02434   0.01620  -0.0721   0.3560   1.0000
   8.750   1.2616   0.02509   0.01688  -0.0704   0.3382   1.0000
   9.000   1.2801   0.02599   0.01765  -0.0691   0.3217   1.0000
   9.250   1.3009   0.02705   0.01860  -0.0684   0.3064   1.0000
   9.500   1.3226   0.02820   0.01975  -0.0678   0.2933   1.0000
   9.750   1.3458   0.02939   0.02094  -0.0675   0.2818   1.0000
  10.000   1.3711   0.03051   0.02196  -0.0675   0.2705   1.0000
  10.250   1.3821   0.03144   0.02306  -0.0653   0.2604   1.0000
  10.500   1.3957   0.03239   0.02408  -0.0635   0.2505   1.0000
  10.750   1.4126   0.03316   0.02474  -0.0623   0.2401   1.0000
  11.000   1.4110   0.03400   0.02585  -0.0583   0.2320   1.0000
  11.250   1.4262   0.03486   0.02669  -0.0569   0.2238   1.0000
  11.500   1.4293   0.03586   0.02790  -0.0539   0.2163   1.0000
  11.750   1.4413   0.03681   0.02884  -0.0522   0.2086   1.0000
  12.000   1.4434   0.03792   0.03014  -0.0494   0.2011   1.0000
  12.250   1.4507   0.03903   0.03129  -0.0474   0.1933   1.0000
  12.500   1.4524   0.04024   0.03261  -0.0450   0.1851   1.0000
  12.750   1.4531   0.04175   0.03425  -0.0426   0.1767   1.0000
  13.000   1.4584   0.04309   0.03547  -0.0409   0.1666   1.0000
  13.250   1.4477   0.04512   0.03775  -0.0381   0.1581   1.0000
  13.500   1.4418   0.04721   0.03991  -0.0360   0.1482   1.0000
  13.750   1.4376   0.04927   0.04190  -0.0343   0.1377   1.0000
  14.000   1.4230   0.05213   0.04500  -0.0325   0.1287   1.0000
  14.250   1.4120   0.05512   0.04809  -0.0312   0.1194   1.0000
  14.500   1.4044   0.05792   0.05081  -0.0303   0.1106   1.0000
  14.750   1.3909   0.06165   0.05477  -0.0298   0.1027   1.0000
  15.000   1.3827   0.06515   0.05831  -0.0295   0.0956   1.0000
  15.250   1.3736   0.06889   0.06213  -0.0296   0.0889   1.0000
  15.500   1.3653   0.07294   0.06631  -0.0299   0.0829   1.0000
  15.750   1.3577   0.07695   0.07037  -0.0305   0.0776   1.0000
  16.000   1.3509   0.08117   0.07467  -0.0311   0.0726   1.0000
  16.250   1.3424   0.08573   0.07936  -0.0322   0.0683   1.0000
  16.500   1.3412   0.08926   0.08279  -0.0327   0.0638   1.0000
  16.750   1.3294   0.09474   0.08857  -0.0344   0.0611   1.0000
  17.000   1.3233   0.09935   0.09331  -0.0358   0.0582   1.0000
  17.250   1.3318   0.10162   0.09541  -0.0355   0.0545   1.0000
  17.500   1.3178   0.10783   0.10194  -0.0381   0.0534   1.0000
  17.750   1.3028   0.11439   0.10876  -0.0411   0.0523   1.0000
  18.000   1.2867   0.12135   0.11598  -0.0446   0.0515   1.0000
  18.250   1.2675   0.12919   0.12406  -0.0490   0.0510   1.0000
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