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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 200,000
Max Cl/Cd: 81.61 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3513-il-200000.txt
Download as CSV file: xf-hq3513-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/13 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2467   0.09011   0.08709  -0.0521   0.9873   0.0564
  -9.250  -0.2414   0.08469   0.08168  -0.0563   0.9847   0.0585
  -9.000  -0.2507   0.07728   0.07430  -0.0644   0.9809   0.0613
  -8.750  -0.2721   0.06783   0.06484  -0.0758   0.9744   0.0620
  -8.500  -0.2928   0.06069   0.05759  -0.0850   0.9665   0.0621
  -8.250  -0.3021   0.05468   0.05136  -0.0917   0.9577   0.0623
  -8.000  -0.3054   0.04617   0.04280  -0.0949   0.9524   0.0633
  -7.750  -0.3988   0.04066   0.03593  -0.0952   0.9485   0.0325
  -7.500  -0.3739   0.03671   0.03151  -0.0975   0.9440   0.0319
  -7.250  -0.3465   0.03178   0.02596  -0.1005   0.9413   0.0323
  -7.000  -0.3295   0.03024   0.02444  -0.1000   0.9335   0.0342
  -6.750  -0.2967   0.02828   0.02221  -0.1019   0.9301   0.0360
  -6.500  -0.2615   0.02562   0.01908  -0.1040   0.9278   0.0381
  -6.250  -0.2336   0.02410   0.01712  -0.1040   0.9228   0.0402
  -6.000  -0.2079   0.02219   0.01518  -0.1042   0.9174   0.0440
  -5.750  -0.1729   0.02125   0.01400  -0.1056   0.9143   0.0513
  -5.500  -0.1374   0.02015   0.01289  -0.1073   0.9120   0.0596
  -5.250  -0.1168   0.01939   0.01207  -0.1062   0.9045   0.0661
  -5.000  -0.0847   0.01910   0.01167  -0.1071   0.9004   0.0747
  -4.750  -0.0519   0.01805   0.01066  -0.1082   0.8975   0.0826
  -4.500  -0.0282   0.01770   0.01022  -0.1074   0.8910   0.0883
  -4.250  -0.0014   0.01686   0.00943  -0.1072   0.8859   0.0943
  -4.000   0.0308   0.01632   0.00883  -0.1080   0.8826   0.1036
  -3.750   0.0530   0.01580   0.00838  -0.1071   0.8759   0.1152
  -3.500   0.0795   0.01518   0.00785  -0.1070   0.8706   0.1365
  -3.250   0.1069   0.01386   0.00721  -0.1076   0.8670   0.2758
  -3.000   0.1227   0.01313   0.00745  -0.1058   0.8595   0.5274
  -2.750   0.1503   0.01311   0.00750  -0.1052   0.8547   0.5924
  -2.500   0.1810   0.01312   0.00749  -0.1051   0.8514   0.6298
  -2.250   0.2026   0.01335   0.00770  -0.1036   0.8437   0.6555
  -2.000   0.2309   0.01338   0.00770  -0.1031   0.8390   0.6768
  -1.750   0.2608   0.01338   0.00764  -0.1029   0.8351   0.6949
  -1.500   0.2824   0.01356   0.00781  -0.1014   0.8271   0.7124
  -1.250   0.3095   0.01359   0.00786  -0.1004   0.8227   0.7345
  -1.000   0.3320   0.01372   0.00801  -0.0987   0.8160   0.7536
  -0.750   0.3581   0.01365   0.00790  -0.0978   0.8095   0.7675
  -0.500   0.3860   0.01351   0.00770  -0.0973   0.8035   0.7792
  -0.250   0.4119   0.01340   0.00755  -0.0967   0.7953   0.7890
   0.000   0.4414   0.01319   0.00728  -0.0965   0.7897   0.7962
   0.250   0.4666   0.01314   0.00720  -0.0960   0.7811   0.8054
   0.500   0.4966   0.01292   0.00693  -0.0959   0.7759   0.8127
   0.750   0.5205   0.01288   0.00689  -0.0951   0.7666   0.8218
   1.000   0.5500   0.01266   0.00662  -0.0950   0.7605   0.8301
   1.250   0.5737   0.01259   0.00657  -0.0941   0.7510   0.8393
   1.500   0.6024   0.01246   0.00640  -0.0940   0.7446   0.8492
   1.750   0.6259   0.01238   0.00636  -0.0930   0.7358   0.8591
   2.000   0.6529   0.01225   0.00622  -0.0926   0.7284   0.8697
   2.250   0.6777   0.01214   0.00614  -0.0918   0.7195   0.8820
   2.500   0.7028   0.01205   0.00608  -0.0911   0.7110   0.8958
   2.750   0.7297   0.01190   0.00595  -0.0905   0.7025   0.9112
   3.000   0.7578   0.01180   0.00591  -0.0904   0.6918   0.9319
   3.250   0.7966   0.01171   0.00584  -0.0927   0.6810   0.9616
   3.500   0.8346   0.01167   0.00576  -0.0949   0.6699   1.0000
   3.750   0.8625   0.01172   0.00578  -0.0952   0.6574   1.0000
   4.000   0.8895   0.01178   0.00582  -0.0953   0.6434   1.0000
   4.250   0.9161   0.01185   0.00585  -0.0952   0.6282   1.0000
   4.500   0.9422   0.01194   0.00589  -0.0949   0.6118   1.0000
   4.750   0.9664   0.01205   0.00599  -0.0942   0.5921   1.0000
   5.000   0.9899   0.01219   0.00606  -0.0934   0.5695   1.0000
   5.250   1.0120   0.01240   0.00618  -0.0923   0.5431   1.0000
   5.500   1.0323   0.01270   0.00635  -0.0909   0.5117   1.0000
   5.750   1.0505   0.01314   0.00658  -0.0892   0.4771   1.0000
   6.000   1.0673   0.01367   0.00692  -0.0873   0.4415   1.0000
   6.250   1.0835   0.01429   0.00734  -0.0854   0.4106   1.0000
   6.500   1.1002   0.01492   0.00780  -0.0836   0.3860   1.0000
   6.750   1.1182   0.01550   0.00829  -0.0821   0.3654   1.0000
   7.000   1.1365   0.01608   0.00878  -0.0807   0.3488   1.0000
   7.250   1.1552   0.01664   0.00928  -0.0793   0.3348   1.0000
   7.500   1.1739   0.01720   0.00979  -0.0780   0.3227   1.0000
   7.750   1.1923   0.01781   0.01033  -0.0767   0.3114   1.0000
   8.000   1.2101   0.01833   0.01086  -0.0752   0.3006   1.0000
   8.250   1.2278   0.01889   0.01142  -0.0737   0.2906   1.0000
   8.500   1.2463   0.01956   0.01202  -0.0725   0.2816   1.0000
   8.750   1.2633   0.02009   0.01264  -0.0709   0.2727   1.0000
   9.000   1.2812   0.02074   0.01329  -0.0696   0.2641   1.0000
   9.250   1.2972   0.02136   0.01393  -0.0680   0.2553   1.0000
   9.500   1.3131   0.02198   0.01463  -0.0664   0.2468   1.0000
   9.750   1.3295   0.02271   0.01531  -0.0650   0.2384   1.0000
  10.000   1.3412   0.02329   0.01607  -0.0628   0.2296   1.0000
  10.250   1.3541   0.02403   0.01681  -0.0610   0.2210   1.0000
  10.500   1.3638   0.02471   0.01760  -0.0588   0.2117   1.0000
  10.750   1.3728   0.02549   0.01847  -0.0566   0.2017   1.0000
  11.000   1.3806   0.02637   0.01937  -0.0545   0.1918   1.0000
  11.250   1.3876   0.02731   0.02036  -0.0524   0.1812   1.0000
  11.500   1.3947   0.02831   0.02147  -0.0505   0.1691   1.0000
  11.750   1.4020   0.02946   0.02267  -0.0488   0.1572   1.0000
  12.000   1.4084   0.03075   0.02399  -0.0472   0.1453   1.0000
  12.250   1.4141   0.03221   0.02546  -0.0456   0.1347   1.0000
  12.500   1.4180   0.03386   0.02710  -0.0440   0.1244   1.0000
  12.750   1.4224   0.03557   0.02884  -0.0427   0.1139   1.0000
  13.000   1.4278   0.03728   0.03061  -0.0415   0.1042   1.0000
  13.250   1.4310   0.03923   0.03261  -0.0403   0.0959   1.0000
  13.500   1.4311   0.04151   0.03490  -0.0392   0.0878   1.0000
  13.750   1.4348   0.04359   0.03709  -0.0383   0.0788   1.0000
  14.000   1.4351   0.04606   0.03963  -0.0375   0.0701   1.0000
  14.250   1.4317   0.04902   0.04262  -0.0369   0.0599   1.0000
  14.500   1.4244   0.05259   0.04620  -0.0364   0.0492   1.0000
  14.750   1.4106   0.05710   0.05069  -0.0362   0.0382   1.0000
  15.000   1.3962   0.06196   0.05559  -0.0364   0.0323   1.0000
  15.250   1.3827   0.06696   0.06065  -0.0371   0.0286   1.0000
  15.500   1.3688   0.07227   0.06607  -0.0381   0.0261   1.0000
  15.750   1.3585   0.07733   0.07127  -0.0394   0.0240   1.0000
  16.000   1.3463   0.08286   0.07692  -0.0411   0.0228   1.0000
  16.250   1.3320   0.08889   0.08305  -0.0432   0.0220   1.0000
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