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HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 200,000
Max Cl/Cd: 80.04 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3514-il-200000.txt
Download as CSV file: xf-hq3514-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2581   0.10327   0.10014  -0.0504   0.9916   0.0684
 -10.500  -0.2768   0.09596   0.09285  -0.0585   0.9882   0.0721
 -10.250  -0.2971   0.08708   0.08399  -0.0679   0.9850   0.0726
 -10.000  -0.2696   0.08314   0.08004  -0.0657   0.9836   0.0744
  -9.750  -0.2436   0.08107   0.07794  -0.0657   0.9808   0.0770
  -9.500  -0.2365   0.07650   0.07336  -0.0688   0.9764   0.0803
  -9.250  -0.4620   0.05671   0.05298  -0.0917   0.9705   0.0497
  -9.000  -0.4608   0.05120   0.04725  -0.0949   0.9611   0.0488
  -8.750  -0.4524   0.04406   0.03961  -0.1002   0.9560   0.0477
  -8.500  -0.4486   0.03949   0.03456  -0.1005   0.9459   0.0480
  -8.250  -0.4247   0.03536   0.02966  -0.1034   0.9422   0.0502
  -8.000  -0.4121   0.03200   0.02590  -0.1029   0.9340   0.0517
  -7.750  -0.3811   0.03037   0.02425  -0.1047   0.9302   0.0538
  -7.500  -0.3473   0.02899   0.02267  -0.1066   0.9275   0.0571
  -7.250  -0.3256   0.02748   0.02080  -0.1061   0.9208   0.0593
  -7.000  -0.2997   0.02575   0.01870  -0.1063   0.9157   0.0617
  -6.750  -0.2678   0.02426   0.01720  -0.1077   0.9128   0.0648
  -6.500  -0.2334   0.02312   0.01592  -0.1091   0.9105   0.0679
  -6.250  -0.2148   0.02253   0.01516  -0.1074   0.9018   0.0707
  -6.000  -0.1834   0.02127   0.01372  -0.1081   0.8982   0.0740
  -5.750  -0.1507   0.02009   0.01256  -0.1091   0.8955   0.0777
  -5.500  -0.1306   0.01967   0.01209  -0.1077   0.8875   0.0817
  -5.250  -0.1003   0.01918   0.01144  -0.1080   0.8834   0.0859
  -5.000  -0.0711   0.01792   0.01027  -0.1083   0.8804   0.0915
  -4.750  -0.0503   0.01758   0.00993  -0.1072   0.8732   0.0973
  -4.500  -0.0238   0.01686   0.00921  -0.1069   0.8685   0.1041
  -4.250   0.0049   0.01624   0.00860  -0.1072   0.8653   0.1129
  -4.000   0.0259   0.01582   0.00824  -0.1062   0.8590   0.1233
  -3.750   0.0513   0.01533   0.00782  -0.1060   0.8539   0.1397
  -3.500   0.0791   0.01464   0.00742  -0.1062   0.8503   0.1987
  -3.250   0.0959   0.01342   0.00735  -0.1053   0.8445   0.4622
  -3.000   0.1201   0.01341   0.00749  -0.1043   0.8389   0.5484
  -2.750   0.1489   0.01343   0.00753  -0.1039   0.8352   0.5892
  -2.500   0.1750   0.01358   0.00769  -0.1032   0.8302   0.6157
  -2.250   0.1994   0.01377   0.00784  -0.1022   0.8237   0.6371
  -2.000   0.2286   0.01381   0.00783  -0.1019   0.8197   0.6532
  -1.750   0.2560   0.01391   0.00791  -0.1014   0.8153   0.6671
  -1.500   0.2795   0.01406   0.00805  -0.1004   0.8085   0.6796
  -1.250   0.3088   0.01401   0.00795  -0.1002   0.8039   0.6920
  -1.000   0.3355   0.01407   0.00796  -0.0996   0.7986   0.7048
  -0.750   0.3599   0.01413   0.00805  -0.0986   0.7921   0.7160
  -0.500   0.3888   0.01405   0.00794  -0.0983   0.7878   0.7266
  -0.250   0.4150   0.01409   0.00795  -0.0979   0.7822   0.7367
   0.000   0.4407   0.01405   0.00793  -0.0972   0.7760   0.7440
   0.250   0.4715   0.01390   0.00771  -0.0975   0.7715   0.7530
   0.500   0.4955   0.01390   0.00776  -0.0966   0.7645   0.7598
   0.750   0.5244   0.01381   0.00762  -0.0967   0.7587   0.7683
   1.000   0.5541   0.01366   0.00746  -0.0967   0.7543   0.7749
   1.250   0.5782   0.01370   0.00752  -0.0960   0.7461   0.7842
   1.500   0.6072   0.01351   0.00732  -0.0958   0.7403   0.7925
   1.750   0.6316   0.01350   0.00734  -0.0951   0.7320   0.8023
   2.000   0.6602   0.01335   0.00718  -0.0949   0.7253   0.8119
   2.250   0.6846   0.01329   0.00716  -0.0941   0.7164   0.8211
   2.500   0.7141   0.01312   0.00694  -0.0941   0.7086   0.8315
   2.750   0.7368   0.01302   0.00693  -0.0928   0.6978   0.8417
   3.000   0.7626   0.01288   0.00678  -0.0921   0.6880   0.8529
   3.250   0.7882   0.01272   0.00664  -0.0913   0.6776   0.8655
   3.500   0.8103   0.01262   0.00660  -0.0900   0.6655   0.8797
   3.750   0.8330   0.01249   0.00651  -0.0887   0.6530   0.8956
   4.000   0.8572   0.01236   0.00641  -0.0877   0.6407   0.9148
   4.250   0.8864   0.01224   0.00634  -0.0878   0.6261   0.9427
   4.500   0.9243   0.01219   0.00631  -0.0900   0.6076   1.0000
   4.750   0.9515   0.01229   0.00636  -0.0903   0.5905   1.0000
   5.000   0.9775   0.01241   0.00643  -0.0902   0.5717   1.0000
   5.500   1.0253   0.01281   0.00666  -0.0891   0.5283   1.0000
   6.000   1.0684   0.01349   0.00709  -0.0871   0.4833   1.0000
   6.250   1.0885   0.01395   0.00740  -0.0858   0.4619   1.0000
   6.500   1.1080   0.01447   0.00778  -0.0845   0.4414   1.0000
   6.750   1.1267   0.01497   0.00822  -0.0831   0.4210   1.0000
   7.000   1.1448   0.01546   0.00865  -0.0816   0.4013   1.0000
   7.250   1.1618   0.01593   0.00908  -0.0799   0.3819   1.0000
   7.500   1.1773   0.01638   0.00950  -0.0780   0.3621   1.0000
   7.750   1.1900   0.01687   0.00994  -0.0756   0.3427   1.0000
   8.000   1.2002   0.01751   0.01047  -0.0728   0.3250   1.0000
   8.250   1.2105   0.01827   0.01112  -0.0702   0.3083   1.0000
   8.500   1.2220   0.01909   0.01185  -0.0679   0.2924   1.0000
   8.750   1.2344   0.01990   0.01261  -0.0658   0.2773   1.0000
   9.000   1.2472   0.02071   0.01339  -0.0639   0.2635   1.0000
   9.250   1.2598   0.02151   0.01415  -0.0620   0.2509   1.0000
   9.500   1.2717   0.02233   0.01491  -0.0601   0.2396   1.0000
   9.750   1.2842   0.02304   0.01568  -0.0583   0.2286   1.0000
  10.000   1.2974   0.02383   0.01651  -0.0566   0.2193   1.0000
  10.250   1.3092   0.02472   0.01735  -0.0549   0.2112   1.0000
  10.500   1.3226   0.02552   0.01824  -0.0535   0.2029   1.0000
  10.750   1.3337   0.02653   0.01918  -0.0519   0.1957   1.0000
  11.000   1.3467   0.02741   0.02018  -0.0505   0.1885   1.0000
  11.250   1.3583   0.02850   0.02121  -0.0491   0.1822   1.0000
  11.500   1.3709   0.02947   0.02232  -0.0478   0.1760   1.0000
  11.750   1.3813   0.03061   0.02346  -0.0464   0.1697   1.0000
  12.000   1.3911   0.03179   0.02472  -0.0451   0.1627   1.0000
  12.250   1.3981   0.03312   0.02607  -0.0436   0.1553   1.0000
  12.500   1.4054   0.03447   0.02753  -0.0423   0.1479   1.0000
  12.750   1.4108   0.03598   0.02909  -0.0410   0.1406   1.0000
  13.000   1.4176   0.03746   0.03072  -0.0399   0.1331   1.0000
  13.250   1.4208   0.03926   0.03254  -0.0388   0.1255   1.0000
  13.500   1.4267   0.04093   0.03438  -0.0380   0.1155   1.0000
  13.750   1.4298   0.04295   0.03648  -0.0372   0.1042   1.0000
  14.000   1.4301   0.04538   0.03892  -0.0364   0.0908   1.0000
  14.250   1.4262   0.04834   0.04184  -0.0357   0.0775   1.0000
  14.500   1.4203   0.05166   0.04514  -0.0352   0.0669   1.0000
  14.750   1.4137   0.05523   0.04873  -0.0348   0.0592   1.0000
  15.000   1.4038   0.05931   0.05281  -0.0347   0.0543   1.0000
  15.250   1.3973   0.06319   0.05679  -0.0348   0.0493   1.0000
  15.500   1.3836   0.06812   0.06174  -0.0354   0.0461   1.0000
  15.750   1.3776   0.07227   0.06604  -0.0360   0.0427   1.0000
  16.000   1.3673   0.07713   0.07098  -0.0371   0.0401   1.0000
  16.250   1.3538   0.08254   0.07640  -0.0384   0.0379   1.0000
  16.500   1.3482   0.08706   0.08109  -0.0396   0.0358   1.0000
  16.750   1.3416   0.09177   0.08589  -0.0410   0.0340   1.0000
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