Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 200,000
Max Cl/Cd: 71.39 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3514-il-200000-n5.txt
Download as CSV file: xf-hq3514-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3787   0.10920   0.10545  -0.0533   1.0000   0.0204
 -12.000  -0.6716   0.04875   0.04454  -0.0847   1.0000   0.0198
 -11.750  -0.6676   0.04462   0.04027  -0.0902   0.9911   0.0202
 -11.500  -0.6527   0.04194   0.03748  -0.0950   0.9837   0.0206
 -11.250  -0.6415   0.03915   0.03452  -0.0990   0.9742   0.0211
 -11.000  -0.6290   0.03655   0.03166  -0.1019   0.9649   0.0218
 -10.750  -0.6145   0.03372   0.02846  -0.1043   0.9576   0.0231
 -10.500  -0.6023   0.03081   0.02505  -0.1054   0.9486   0.0245
 -10.250  -0.5788   0.03001   0.02423  -0.1062   0.9420   0.0253
 -10.000  -0.5564   0.02916   0.02329  -0.1067   0.9346   0.0264
  -9.750  -0.5352   0.02780   0.02169  -0.1070   0.9280   0.0277
  -9.500  -0.5162   0.02631   0.01985  -0.1068   0.9200   0.0293
  -9.250  -0.4929   0.02531   0.01873  -0.1070   0.9140   0.0307
  -9.000  -0.4707   0.02473   0.01810  -0.1067   0.9064   0.0319
  -8.750  -0.4451   0.02394   0.01716  -0.1070   0.9012   0.0336
  -8.500  -0.4234   0.02305   0.01604  -0.1064   0.8938   0.0354
  -8.250  -0.3991   0.02201   0.01480  -0.1063   0.8885   0.0369
  -8.000  -0.3748   0.02138   0.01413  -0.1062   0.8828   0.0384
  -7.750  -0.3504   0.02084   0.01352  -0.1059   0.8767   0.0401
  -7.500  -0.3243   0.02014   0.01267  -0.1058   0.8720   0.0421
  -7.250  -0.3003   0.01948   0.01185  -0.1053   0.8656   0.0438
  -7.000  -0.2759   0.01876   0.01106  -0.1050   0.8601   0.0457
  -6.750  -0.2497   0.01827   0.01052  -0.1050   0.8557   0.0478
  -6.500  -0.2257   0.01782   0.01003  -0.1045   0.8490   0.0500
  -6.250  -0.2003   0.01732   0.00942  -0.1041   0.8434   0.0524
  -6.000  -0.1751   0.01684   0.00884  -0.1038   0.8378   0.0548
  -5.750  -0.1509   0.01637   0.00839  -0.1033   0.8310   0.0578
  -5.500  -0.1247   0.01599   0.00794  -0.1031   0.8259   0.0611
  -5.250  -0.0996   0.01565   0.00754  -0.1028   0.8200   0.0644
  -5.000  -0.0744   0.01523   0.00711  -0.1025   0.8147   0.0685
  -4.750  -0.0477   0.01491   0.00675  -0.1024   0.8105   0.0733
  -4.500  -0.0219   0.01466   0.00643  -0.1021   0.8048   0.0779
  -4.250   0.0038   0.01429   0.00606  -0.1019   0.7992   0.0839
  -4.000   0.0310   0.01403   0.00573  -0.1019   0.7950   0.0912
  -3.750   0.0570   0.01372   0.00543  -0.1017   0.7899   0.0996
  -3.500   0.0834   0.01343   0.00514  -0.1016   0.7848   0.1117
  -3.000   0.1357   0.01257   0.00465  -0.1016   0.7750   0.2150
  -2.750   0.1608   0.01202   0.00443  -0.1016   0.7694   0.3075
  -2.500   0.1854   0.01143   0.00443  -0.1013   0.7651   0.4720
  -2.250   0.2129   0.01137   0.00439  -0.1011   0.7609   0.5148
  -2.000   0.2395   0.01134   0.00440  -0.1008   0.7549   0.5449
  -1.750   0.2670   0.01131   0.00437  -0.1005   0.7494   0.5662
  -1.500   0.2941   0.01131   0.00437  -0.1002   0.7430   0.5855
  -1.250   0.3211   0.01132   0.00438  -0.0999   0.7363   0.6032
  -1.000   0.3493   0.01135   0.00435  -0.0997   0.7312   0.6197
  -0.750   0.3757   0.01140   0.00442  -0.0993   0.7245   0.6335
  -0.500   0.4034   0.01143   0.00441  -0.0992   0.7186   0.6456
  -0.250   0.4313   0.01148   0.00441  -0.0991   0.7133   0.6571
   0.000   0.4580   0.01151   0.00447  -0.0988   0.7072   0.6651
   0.250   0.4861   0.01155   0.00445  -0.0987   0.7015   0.6743
   0.750   0.5403   0.01162   0.00450  -0.0983   0.6881   0.6898
   1.000   0.5679   0.01165   0.00452  -0.0981   0.6823   0.6960
   1.250   0.5944   0.01170   0.00459  -0.0979   0.6747   0.7036
   1.500   0.6218   0.01172   0.00460  -0.0977   0.6681   0.7105
   1.750   0.6479   0.01177   0.00468  -0.0973   0.6596   0.7184
   2.000   0.6749   0.01181   0.00470  -0.0971   0.6519   0.7260
   2.250   0.7004   0.01185   0.00479  -0.0966   0.6417   0.7340
   2.500   0.7261   0.01189   0.00482  -0.0961   0.6301   0.7416
   2.750   0.7514   0.01194   0.00487  -0.0955   0.6170   0.7492
   3.000   0.7765   0.01200   0.00491  -0.0949   0.6027   0.7570
   3.250   0.8009   0.01207   0.00499  -0.0942   0.5868   0.7650
   3.500   0.8251   0.01216   0.00508  -0.0934   0.5686   0.7735
   3.750   0.8483   0.01227   0.00517  -0.0925   0.5478   0.7823
   4.000   0.8706   0.01243   0.00526  -0.0914   0.5248   0.7913
   4.250   0.8919   0.01264   0.00540  -0.0901   0.5006   0.8012
   4.500   0.9115   0.01292   0.00557  -0.0886   0.4775   0.8117
   4.750   0.9314   0.01322   0.00580  -0.0872   0.4578   0.8235
   5.000   0.9520   0.01350   0.00605  -0.0859   0.4426   0.8372
   5.250   0.9719   0.01378   0.00633  -0.0845   0.4278   0.8538
   5.500   0.9914   0.01404   0.00661  -0.0830   0.4130   0.8777
   5.750   1.0175   0.01426   0.00690  -0.0829   0.3959   0.9430
   6.000   1.0395   0.01456   0.00720  -0.0821   0.3774   1.0000
   6.250   1.0594   0.01495   0.00753  -0.0810   0.3550   1.0000
   6.500   1.0761   0.01543   0.00790  -0.0793   0.3340   1.0000
   6.750   1.0907   0.01595   0.00830  -0.0773   0.3179   1.0000
   7.000   1.1045   0.01650   0.00878  -0.0752   0.3045   1.0000
   7.250   1.1196   0.01704   0.00928  -0.0733   0.2928   1.0000
   7.500   1.1361   0.01756   0.00979  -0.0717   0.2823   1.0000
   7.750   1.1511   0.01814   0.01035  -0.0700   0.2724   1.0000
   8.000   1.1676   0.01868   0.01092  -0.0684   0.2617   1.0000
   8.250   1.1836   0.01925   0.01150  -0.0669   0.2507   1.0000
   8.500   1.1983   0.01988   0.01212  -0.0653   0.2389   1.0000
   8.750   1.2126   0.02055   0.01278  -0.0636   0.2264   1.0000
   9.000   1.2265   0.02125   0.01348  -0.0620   0.2130   1.0000
   9.250   1.2401   0.02200   0.01422  -0.0605   0.2012   1.0000
   9.500   1.2524   0.02285   0.01504  -0.0588   0.1905   1.0000
   9.750   1.2637   0.02378   0.01594  -0.0571   0.1819   1.0000
  10.000   1.2759   0.02470   0.01687  -0.0556   0.1741   1.0000
  10.250   1.2867   0.02572   0.01791  -0.0540   0.1681   1.0000
  10.500   1.3000   0.02664   0.01888  -0.0527   0.1619   1.0000
  10.750   1.3102   0.02776   0.02001  -0.0513   0.1564   1.0000
  11.000   1.3227   0.02876   0.02108  -0.0500   0.1512   1.0000
  11.250   1.3353   0.02978   0.02217  -0.0489   0.1458   1.0000
  11.500   1.3446   0.03103   0.02344  -0.0475   0.1410   1.0000
  11.750   1.3573   0.03209   0.02461  -0.0465   0.1364   1.0000
  12.000   1.3690   0.03323   0.02584  -0.0455   0.1305   1.0000
  12.250   1.3768   0.03467   0.02730  -0.0443   0.1248   1.0000
  12.500   1.3888   0.03584   0.02858  -0.0434   0.1169   1.0000
  12.750   1.3966   0.03736   0.03013  -0.0424   0.1092   1.0000
  13.000   1.4038   0.03897   0.03178  -0.0415   0.0996   1.0000
  13.250   1.4104   0.04069   0.03353  -0.0407   0.0886   1.0000
  13.500   1.4148   0.04268   0.03553  -0.0398   0.0778   1.0000
  13.750   1.4164   0.04499   0.03782  -0.0390   0.0664   1.0000
  14.000   1.4158   0.04760   0.04040  -0.0383   0.0564   1.0000
  14.250   1.4149   0.05034   0.04316  -0.0377   0.0491   1.0000
  14.500   1.4137   0.05322   0.04609  -0.0373   0.0442   1.0000
  14.750   1.4117   0.05629   0.04923  -0.0370   0.0403   1.0000
  15.000   1.4089   0.05958   0.05260  -0.0369   0.0373   1.0000
  15.250   1.4071   0.06286   0.05599  -0.0371   0.0347   1.0000
  15.500   1.4025   0.06661   0.05987  -0.0374   0.0324   1.0000
  15.750   1.3958   0.07079   0.06414  -0.0381   0.0305   1.0000
  16.000   1.3926   0.07463   0.06815  -0.0389   0.0285   1.0000
  16.250   1.3861   0.07908   0.07272  -0.0400   0.0267   1.0000
  16.500   1.3764   0.08417   0.07793  -0.0415   0.0253   1.0000
  16.750   1.3677   0.08928   0.08318  -0.0432   0.0240   1.0000
  17.000   1.3605   0.09430   0.08836  -0.0451   0.0227   1.0000
  17.250   1.3510   0.09980   0.09402  -0.0472   0.0215   1.0000
  17.500   1.3391   0.10582   0.10017  -0.0498   0.0207   1.0000
  17.750   1.3261   0.11217   0.10665  -0.0527   0.0201   1.0000
<< Back to HQ 3.5/14 AIRFOIL (hq3514-il)

Polar data table (+)

Polar graphs


<< Back to HQ 3.5/14 AIRFOIL (hq3514-il)