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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 50,000
Max Cl/Cd: 35.32 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3513-il-50000-n5.txt
Download as CSV file: xf-hq3513-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3379   0.10571   0.09884  -0.0490   1.0000   0.0521
  -9.750  -0.3448   0.10252   0.09575  -0.0490   1.0000   0.0522
  -9.500  -0.3529   0.09945   0.09279  -0.0487   1.0000   0.0518
  -9.250  -0.3638   0.09644   0.08990  -0.0481   1.0000   0.0517
  -9.000  -0.3772   0.09355   0.08716  -0.0473   1.0000   0.0516
  -8.750  -0.3932   0.09067   0.08440  -0.0463   1.0000   0.0514
  -8.500  -0.4116   0.08781   0.08166  -0.0452   1.0000   0.0509
  -8.250  -0.4334   0.08486   0.07882  -0.0441   1.0000   0.0500
  -8.000  -0.4611   0.08163   0.07570  -0.0432   1.0000   0.0490
  -7.750  -0.4875   0.07747   0.07159  -0.0439   1.0000   0.0481
  -7.500  -0.4871   0.07069   0.06462  -0.0511   0.9915   0.0481
  -7.250  -0.4800   0.06454   0.05819  -0.0572   0.9832   0.0485
  -7.000  -0.4709   0.05942   0.05273  -0.0612   0.9751   0.0495
  -6.750  -0.4564   0.05442   0.04727  -0.0648   0.9682   0.0505
  -6.500  -0.4391   0.04984   0.04215  -0.0673   0.9614   0.0516
  -6.250  -0.4149   0.04554   0.03707  -0.0701   0.9562   0.0543
  -6.000  -0.3943   0.04265   0.03376  -0.0710   0.9496   0.0577
  -5.750  -0.3660   0.04060   0.03147  -0.0726   0.9447   0.0626
  -5.500  -0.3383   0.03822   0.02833  -0.0735   0.9395   0.0688
  -5.250  -0.3132   0.03654   0.02663  -0.0740   0.9339   0.0747
  -5.000  -0.2807   0.03487   0.02448  -0.0752   0.9296   0.0834
  -4.750  -0.2551   0.03374   0.02329  -0.0754   0.9242   0.0915
  -4.500  -0.2273   0.03256   0.02184  -0.0752   0.9188   0.0982
  -4.250  -0.1953   0.03164   0.02085  -0.0762   0.9146   0.1088
  -4.000  -0.1717   0.03085   0.02001  -0.0755   0.9087   0.1164
  -3.750  -0.1445   0.03019   0.01917  -0.0754   0.9032   0.1268
  -3.500  -0.1114   0.02941   0.01844  -0.0769   0.8991   0.1448
  -3.250  -0.0905   0.02881   0.01790  -0.0763   0.8922   0.1644
  -3.000  -0.0607   0.02787   0.01724  -0.0776   0.8871   0.2159
  -2.750  -0.0332   0.02642   0.01716  -0.0783   0.8831   0.4434
  -2.500  -0.0203   0.02664   0.01769  -0.0748   0.8752   0.5756
  -2.250   0.0057   0.02697   0.01797  -0.0734   0.8701   0.6501
  -2.000   0.0199   0.02734   0.01829  -0.0702   0.8624   0.6955
  -1.750   0.0376   0.02763   0.01856  -0.0668   0.8564   0.7495
  -1.500   0.0473   0.02781   0.01876  -0.0620   0.8493   0.7950
  -1.250   0.0615   0.02779   0.01872  -0.0582   0.8426   0.8335
  -1.000   0.0883   0.02770   0.01851  -0.0573   0.8376   0.8602
  -0.750   0.1094   0.02775   0.01844  -0.0565   0.8294   0.8782
  -0.500   0.1480   0.02769   0.01821  -0.0585   0.8249   0.8951
  -0.250   0.1764   0.02785   0.01827  -0.0593   0.8169   0.9139
   0.000   0.2228   0.02789   0.01818  -0.0631   0.8117   0.9331
   0.250   0.2676   0.02803   0.01819  -0.0671   0.8054   0.9589
   0.500   0.3054   0.02815   0.01818  -0.0700   0.7980   1.0000
   0.750   0.3322   0.02832   0.01822  -0.0707   0.7904   1.0000
   1.000   0.3605   0.02852   0.01830  -0.0716   0.7826   1.0000
   1.250   0.3868   0.02880   0.01847  -0.0722   0.7743   1.0000
   1.500   0.4195   0.02895   0.01851  -0.0734   0.7672   1.0000
   1.750   0.4436   0.02931   0.01879  -0.0735   0.7580   1.0000
   2.000   0.4821   0.02921   0.01861  -0.0752   0.7512   1.0000
   2.250   0.5077   0.02931   0.01865  -0.0750   0.7392   1.0000
   2.500   0.5386   0.02917   0.01846  -0.0752   0.7276   1.0000
   2.750   0.5823   0.02853   0.01775  -0.0768   0.7191   1.0000
   3.000   0.6089   0.02848   0.01768  -0.0764   0.7066   1.0000
   3.250   0.6326   0.02865   0.01785  -0.0757   0.6944   1.0000
   3.500   0.6594   0.02869   0.01788  -0.0754   0.6831   1.0000
   3.750   0.6986   0.02821   0.01740  -0.0764   0.6753   1.0000
   4.000   0.7211   0.02838   0.01761  -0.0755   0.6622   1.0000
   4.250   0.7451   0.02847   0.01773  -0.0747   0.6490   1.0000
   4.500   0.7702   0.02850   0.01779  -0.0740   0.6355   1.0000
   4.750   0.7956   0.02850   0.01783  -0.0733   0.6217   1.0000
   5.000   0.8211   0.02848   0.01788  -0.0725   0.6073   1.0000
   5.250   0.8465   0.02843   0.01788  -0.0717   0.5916   1.0000
   5.500   0.8722   0.02838   0.01787  -0.0709   0.5753   1.0000
   5.750   0.8991   0.02828   0.01783  -0.0702   0.5583   1.0000
   6.000   0.9240   0.02829   0.01785  -0.0693   0.5395   1.0000
   6.250   0.9454   0.02849   0.01808  -0.0680   0.5189   1.0000
   6.500   0.9723   0.02851   0.01811  -0.0673   0.4990   1.0000
   6.750   0.9956   0.02877   0.01833  -0.0663   0.4781   1.0000
   7.000   1.0182   0.02914   0.01867  -0.0653   0.4578   1.0000
   7.250   1.0423   0.02954   0.01899  -0.0645   0.4388   1.0000
   7.500   1.0639   0.03012   0.01955  -0.0636   0.4208   1.0000
   7.750   1.0836   0.03083   0.02026  -0.0625   0.4040   1.0000
   8.000   1.1034   0.03159   0.02101  -0.0614   0.3883   1.0000
   8.250   1.1234   0.03238   0.02181  -0.0605   0.3739   1.0000
   8.500   1.1433   0.03321   0.02268  -0.0595   0.3602   1.0000
   8.750   1.1641   0.03403   0.02352  -0.0587   0.3474   1.0000
   9.000   1.1802   0.03501   0.02461  -0.0574   0.3349   1.0000
   9.250   1.1964   0.03604   0.02574  -0.0562   0.3231   1.0000
   9.500   1.2135   0.03706   0.02684  -0.0551   0.3117   1.0000
   9.750   1.2322   0.03803   0.02790  -0.0542   0.3007   1.0000
  10.000   1.2498   0.03905   0.02898  -0.0531   0.2897   1.0000
  10.250   1.2601   0.04038   0.03048  -0.0514   0.2789   1.0000
  10.500   1.2738   0.04162   0.03183  -0.0501   0.2685   1.0000
  10.750   1.2902   0.04272   0.03296  -0.0490   0.2579   1.0000
  11.000   1.2956   0.04432   0.03482  -0.0471   0.2479   1.0000
  11.250   1.3033   0.04589   0.03655  -0.0455   0.2382   1.0000
  11.500   1.3162   0.04713   0.03783  -0.0443   0.2285   1.0000
  11.750   1.3141   0.04928   0.04027  -0.0422   0.2197   1.0000
  12.000   1.3194   0.05103   0.04216  -0.0407   0.2110   1.0000
  12.250   1.3214   0.05297   0.04426  -0.0392   0.2024   1.0000
  12.500   1.3190   0.05546   0.04698  -0.0377   0.1944   1.0000
  12.750   1.3250   0.05713   0.04871  -0.0365   0.1863   1.0000
  13.000   1.3135   0.06061   0.05250  -0.0353   0.1791   1.0000
  13.250   1.3186   0.06234   0.05424  -0.0344   0.1714   1.0000
  13.500   1.3022   0.06673   0.05901  -0.0339   0.1651   1.0000
  13.750   1.3077   0.06852   0.06079  -0.0332   0.1578   1.0000
  14.000   1.2858   0.07406   0.06667  -0.0336   0.1524   1.0000
  14.250   1.2862   0.07653   0.06917  -0.0334   0.1455   1.0000
  14.500   1.2655   0.08252   0.07541  -0.0346   0.1409   1.0000
  14.750   1.2444   0.08894   0.08204  -0.0364   0.1364   1.0000
  15.000   1.2477   0.09135   0.08446  -0.0366   0.1297   1.0000
  15.250   1.2090   0.10176   0.09515  -0.0410   0.1276   1.0000
  15.500   1.1411   0.11971   0.11321  -0.0504   0.1274   1.0000
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