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HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 50,000
Max Cl/Cd: 33.1 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3514-il-50000-n5.txt
Download as CSV file: xf-hq3514-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4150   0.09294   0.08626  -0.0574   1.0000   0.0655
  -9.750  -0.4328   0.08925   0.08267  -0.0571   1.0000   0.0653
  -9.500  -0.4547   0.08591   0.07942  -0.0563   1.0000   0.0652
  -9.250  -0.4812   0.08294   0.07656  -0.0550   1.0000   0.0650
  -9.000  -0.5067   0.08068   0.07439  -0.0528   1.0000   0.0647
  -8.750  -0.5325   0.07820   0.07196  -0.0510   1.0000   0.0643
  -8.500  -0.5433   0.07115   0.06464  -0.0581   0.9898   0.0645
  -8.250  -0.5492   0.06465   0.05766  -0.0636   0.9798   0.0653
  -8.000  -0.5336   0.06130   0.05425  -0.0657   0.9738   0.0672
  -7.750  -0.5219   0.05781   0.05051  -0.0674   0.9668   0.0686
  -7.500  -0.5064   0.05393   0.04624  -0.0699   0.9607   0.0701
  -7.250  -0.4929   0.05083   0.04275  -0.0709   0.9539   0.0727
  -7.000  -0.4737   0.04741   0.03873  -0.0727   0.9482   0.0758
  -6.750  -0.4533   0.04439   0.03504  -0.0737   0.9426   0.0778
  -6.500  -0.4318   0.04216   0.03259  -0.0742   0.9370   0.0807
  -6.250  -0.4041   0.04048   0.03071  -0.0754   0.9328   0.0848
  -6.000  -0.3798   0.03876   0.02862  -0.0756   0.9280   0.0883
  -5.750  -0.3556   0.03727   0.02665  -0.0755   0.9226   0.0920
  -5.500  -0.3269   0.03588   0.02522  -0.0763   0.9186   0.0970
  -5.250  -0.2979   0.03477   0.02393  -0.0768   0.9147   0.1020
  -5.000  -0.2763   0.03396   0.02284  -0.0758   0.9090   0.1073
  -4.750  -0.2496   0.03305   0.02204  -0.0759   0.9049   0.1140
  -4.500  -0.2179   0.03232   0.02112  -0.0765   0.9015   0.1218
  -4.250  -0.2005   0.03175   0.02063  -0.0752   0.8954   0.1292
  -4.000  -0.1749   0.03119   0.02004  -0.0752   0.8907   0.1404
  -3.750  -0.1441   0.03060   0.01949  -0.0762   0.8871   0.1550
  -3.500  -0.1243   0.03018   0.01911  -0.0755   0.8812   0.1752
  -3.250  -0.0986   0.02948   0.01856  -0.0760   0.8762   0.2121
  -3.000  -0.0695   0.02813   0.01808  -0.0776   0.8726   0.3397
  -2.750  -0.0560   0.02808   0.01880  -0.0745   0.8664   0.5258
  -2.500  -0.0345   0.02845   0.01921  -0.0725   0.8601   0.5977
  -2.250  -0.0095   0.02885   0.01954  -0.0709   0.8540   0.6515
  -2.000   0.0091   0.02916   0.01977  -0.0684   0.8451   0.6898
  -1.750   0.0328   0.02938   0.01994  -0.0661   0.8386   0.7253
  -1.500   0.0467   0.02958   0.02010  -0.0626   0.8297   0.7559
  -1.250   0.0730   0.02962   0.02006  -0.0608   0.8251   0.7870
  -1.000   0.0796   0.02980   0.02022  -0.0568   0.8160   0.8076
  -0.750   0.1067   0.02975   0.02008  -0.0561   0.8112   0.8274
  -0.500   0.1229   0.02987   0.02013  -0.0543   0.8033   0.8432
  -0.250   0.1501   0.02987   0.02004  -0.0542   0.7975   0.8572
   0.000   0.1812   0.02986   0.01992  -0.0550   0.7922   0.8692
   0.250   0.2023   0.03003   0.02003  -0.0545   0.7837   0.8815
   0.500   0.2414   0.02993   0.01984  -0.0565   0.7793   0.8926
   0.750   0.2631   0.03024   0.02014  -0.0564   0.7700   0.9083
   1.000   0.3047   0.03026   0.02011  -0.0591   0.7651   0.9240
   1.250   0.3399   0.03056   0.02039  -0.0615   0.7571   0.9459
   1.500   0.3853   0.03057   0.02036  -0.0653   0.7504   0.9797
   2.000   0.4470   0.03065   0.02028  -0.0675   0.7336   1.0000
   2.250   0.4704   0.03087   0.02044  -0.0675   0.7220   1.0000
   2.500   0.5160   0.03033   0.01983  -0.0698   0.7160   1.0000
   2.750   0.5375   0.03054   0.01999  -0.0692   0.7030   1.0000
   3.000   0.5630   0.03068   0.02010  -0.0691   0.6917   1.0000
   3.250   0.6025   0.03037   0.01976  -0.0706   0.6850   1.0000
   3.500   0.6211   0.03084   0.02021  -0.0697   0.6727   1.0000
   3.750   0.6639   0.03041   0.01978  -0.0715   0.6675   1.0000
   4.000   0.6800   0.03094   0.02032  -0.0701   0.6543   1.0000
   4.250   0.7000   0.03135   0.02075  -0.0692   0.6422   1.0000
   4.500   0.7411   0.03086   0.02029  -0.0706   0.6358   1.0000
   4.750   0.7576   0.03136   0.02082  -0.0691   0.6223   1.0000
   5.000   0.7773   0.03175   0.02125  -0.0681   0.6096   1.0000
   5.250   0.8033   0.03183   0.02139  -0.0676   0.5984   1.0000
   5.500   0.8400   0.03126   0.02086  -0.0681   0.5885   1.0000
   5.750   0.8625   0.03123   0.02087  -0.0669   0.5733   1.0000
   6.000   0.8877   0.03099   0.02067  -0.0658   0.5573   1.0000
   6.250   0.9034   0.03125   0.02095  -0.0639   0.5383   1.0000
   6.500   0.9252   0.03126   0.02098  -0.0626   0.5202   1.0000
   6.750   0.9503   0.03122   0.02095  -0.0618   0.5033   1.0000
   7.000   0.9768   0.03120   0.02094  -0.0611   0.4868   1.0000
   7.250   1.0033   0.03124   0.02095  -0.0604   0.4698   1.0000
   7.500   1.0287   0.03144   0.02111  -0.0597   0.4524   1.0000
   7.750   1.0519   0.03183   0.02149  -0.0589   0.4350   1.0000
   8.000   1.0725   0.03240   0.02204  -0.0578   0.4177   1.0000
   8.250   1.0898   0.03316   0.02280  -0.0565   0.4005   1.0000
   8.500   1.1042   0.03405   0.02373  -0.0551   0.3837   1.0000
   8.750   1.1173   0.03501   0.02476  -0.0535   0.3676   1.0000
   9.000   1.1304   0.03597   0.02574  -0.0519   0.3521   1.0000
   9.250   1.1446   0.03691   0.02669  -0.0505   0.3376   1.0000
   9.500   1.1597   0.03790   0.02768  -0.0493   0.3239   1.0000
   9.750   1.1755   0.03897   0.02879  -0.0482   0.3110   1.0000
  10.000   1.1923   0.04008   0.02993  -0.0472   0.2988   1.0000
  10.250   1.2125   0.04109   0.03093  -0.0465   0.2874   1.0000
  10.500   1.2300   0.04231   0.03223  -0.0457   0.2767   1.0000
  10.750   1.2443   0.04376   0.03386  -0.0448   0.2670   1.0000
  11.000   1.2685   0.04469   0.03476  -0.0444   0.2578   1.0000
  11.250   1.2722   0.04667   0.03704  -0.0428   0.2495   1.0000
  11.500   1.2938   0.04772   0.03811  -0.0423   0.2416   1.0000
  11.750   1.2949   0.04996   0.04065  -0.0408   0.2345   1.0000
  12.000   1.3150   0.05097   0.04168  -0.0402   0.2271   1.0000
  12.250   1.3082   0.05372   0.04478  -0.0384   0.2204   1.0000
  12.500   1.3218   0.05479   0.04584  -0.0374   0.2124   1.0000
  12.750   1.3083   0.05812   0.04947  -0.0359   0.2056   1.0000
  13.000   1.3134   0.05958   0.05091  -0.0348   0.1971   1.0000
  13.250   1.2995   0.06321   0.05481  -0.0339   0.1901   1.0000
  13.500   1.3027   0.06505   0.05664  -0.0331   0.1821   1.0000
  13.750   1.2888   0.06914   0.06099  -0.0328   0.1757   1.0000
  14.000   1.2960   0.07081   0.06264  -0.0323   0.1681   1.0000
  14.250   1.2767   0.07610   0.06823  -0.0328   0.1629   1.0000
  14.500   1.2873   0.07739   0.06951  -0.0322   0.1549   1.0000
  14.750   1.2625   0.08392   0.07636  -0.0336   0.1505   1.0000
  15.000   1.2426   0.09010   0.08278  -0.0353   0.1453   1.0000
  15.250   1.2467   0.09251   0.08520  -0.0355   0.1381   1.0000
  15.500   1.2054   0.10319   0.09618  -0.0400   0.1351   1.0000
  15.750   1.1345   0.12146   0.11466  -0.0495   0.1333   1.0000
  16.000   1.1777   0.11560   0.10882  -0.0453   0.1238   1.0000
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