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HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il)
Reynolds number: 200,000
Max Cl/Cd: 79.26 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3013-il-200000.txt
Download as CSV file: xf-hq3013-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/13 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3630   0.09312   0.08975  -0.0488   1.0000   0.0590
  -9.500  -0.3823   0.08907   0.08580  -0.0503   1.0000   0.0608
  -8.500  -0.5358   0.04629   0.04188  -0.0767   0.9738   0.0327
  -8.250  -0.5163   0.04064   0.03586  -0.0803   0.9698   0.0320
  -8.000  -0.5045   0.03615   0.03087  -0.0809   0.9613   0.0320
  -7.750  -0.4785   0.03230   0.02637  -0.0831   0.9571   0.0325
  -7.500  -0.4569   0.02875   0.02252  -0.0840   0.9519   0.0338
  -7.250  -0.4275   0.02797   0.02173  -0.0852   0.9466   0.0363
  -7.000  -0.3935   0.02594   0.01929  -0.0870   0.9434   0.0392
  -6.750  -0.3577   0.02341   0.01641  -0.0891   0.9414   0.0423
  -6.500  -0.3334   0.02261   0.01558  -0.0889   0.9347   0.0462
  -6.250  -0.3001   0.02133   0.01412  -0.0903   0.9309   0.0532
  -6.000  -0.2632   0.02061   0.01331  -0.0922   0.9282   0.0607
  -5.750  -0.2267   0.01953   0.01221  -0.0943   0.9260   0.0688
  -5.500  -0.2045   0.01936   0.01188  -0.0933   0.9180   0.0750
  -5.250  -0.1726   0.01825   0.01084  -0.0944   0.9144   0.0825
  -5.000  -0.1368   0.01771   0.01017  -0.0958   0.9117   0.0892
  -4.750  -0.1162   0.01690   0.00946  -0.0947   0.9043   0.0956
  -4.500  -0.0862   0.01632   0.00883  -0.0951   0.8997   0.1045
  -4.250  -0.0542   0.01563   0.00817  -0.0959   0.8965   0.1183
  -4.000  -0.0340   0.01509   0.00775  -0.0948   0.8888   0.1365
  -3.750  -0.0074   0.01419   0.00720  -0.0950   0.8839   0.1990
  -3.500   0.0143   0.01278   0.00692  -0.0946   0.8796   0.4606
  -3.250   0.0355   0.01280   0.00711  -0.0931   0.8718   0.5457
  -3.000   0.0653   0.01280   0.00709  -0.0930   0.8676   0.5896
  -2.750   0.0914   0.01291   0.00718  -0.0922   0.8619   0.6177
  -2.500   0.1172   0.01299   0.00725  -0.0914   0.8555   0.6394
  -2.250   0.1475   0.01296   0.00717  -0.0913   0.8514   0.6571
  -2.000   0.1712   0.01308   0.00727  -0.0902   0.8441   0.6726
  -1.750   0.1988   0.01310   0.00727  -0.0896   0.8385   0.6895
  -1.500   0.2261   0.01318   0.00734  -0.0888   0.8337   0.7098
  -1.250   0.2488   0.01332   0.00749  -0.0874   0.8260   0.7263
  -1.000   0.2777   0.01325   0.00739  -0.0871   0.8214   0.7366
  -0.750   0.3024   0.01331   0.00743  -0.0864   0.8144   0.7471
  -0.500   0.3296   0.01329   0.00738  -0.0860   0.8085   0.7593
  -0.250   0.3579   0.01322   0.00729  -0.0856   0.8039   0.7681
   0.000   0.3825   0.01324   0.00730  -0.0850   0.7959   0.7762
   0.250   0.4121   0.01309   0.00712  -0.0850   0.7908   0.7832
   0.500   0.4372   0.01304   0.00705  -0.0844   0.7816   0.7916
   0.750   0.4672   0.01280   0.00676  -0.0842   0.7749   0.7995
   1.000   0.4916   0.01273   0.00671  -0.0834   0.7650   0.8081
   1.250   0.5213   0.01260   0.00652  -0.0834   0.7593   0.8175
   1.500   0.5446   0.01257   0.00655  -0.0825   0.7500   0.8272
   1.750   0.5734   0.01244   0.00639  -0.0823   0.7436   0.8379
   2.000   0.5974   0.01238   0.00638  -0.0815   0.7339   0.8499
   2.250   0.6230   0.01224   0.00627  -0.0807   0.7254   0.8623
   2.500   0.6483   0.01206   0.00612  -0.0798   0.7160   0.8766
   2.750   0.6720   0.01192   0.00604  -0.0787   0.7050   0.8939
   3.000   0.6983   0.01174   0.00590  -0.0780   0.6946   0.9134
   3.250   0.7323   0.01158   0.00575  -0.0789   0.6844   0.9394
   3.500   0.7755   0.01148   0.00569  -0.0821   0.6710   0.9766
   3.750   0.8075   0.01150   0.00568  -0.0833   0.6575   1.0000
   4.000   0.8342   0.01155   0.00570  -0.0833   0.6435   1.0000
   4.250   0.8606   0.01162   0.00573  -0.0831   0.6283   1.0000
   4.500   0.8864   0.01171   0.00576  -0.0827   0.6117   1.0000
   4.750   0.9117   0.01182   0.00581  -0.0822   0.5939   1.0000
   5.000   0.9354   0.01196   0.00593  -0.0815   0.5729   1.0000
   5.250   0.9589   0.01214   0.00603  -0.0806   0.5509   1.0000
   5.500   0.9813   0.01238   0.00621  -0.0796   0.5263   1.0000
   5.750   1.0028   0.01268   0.00641  -0.0784   0.5001   1.0000
   6.000   1.0229   0.01306   0.00666  -0.0771   0.4720   1.0000
   6.250   1.0420   0.01352   0.00697  -0.0756   0.4435   1.0000
   6.500   1.0603   0.01403   0.00736  -0.0740   0.4155   1.0000
   6.750   1.0779   0.01456   0.00778  -0.0723   0.3881   1.0000
   7.000   1.0951   0.01513   0.00824  -0.0706   0.3624   1.0000
   7.250   1.1111   0.01574   0.00872  -0.0688   0.3394   1.0000
   7.500   1.1276   0.01633   0.00925  -0.0671   0.3174   1.0000
   7.750   1.1428   0.01698   0.00980  -0.0652   0.2982   1.0000
   8.000   1.1576   0.01766   0.01039  -0.0632   0.2811   1.0000
   8.250   1.1713   0.01832   0.01098  -0.0611   0.2655   1.0000
   8.500   1.1848   0.01896   0.01159  -0.0590   0.2511   1.0000
   8.750   1.1982   0.01960   0.01223  -0.0569   0.2373   1.0000
   9.000   1.2117   0.02025   0.01289  -0.0549   0.2242   1.0000
   9.250   1.2251   0.02094   0.01359  -0.0529   0.2123   1.0000
   9.500   1.2377   0.02169   0.01434  -0.0510   0.2010   1.0000
   9.750   1.2491   0.02254   0.01514  -0.0490   0.1905   1.0000
  10.000   1.2611   0.02335   0.01598  -0.0471   0.1798   1.0000
  10.250   1.2730   0.02419   0.01690  -0.0454   0.1694   1.0000
  10.500   1.2832   0.02519   0.01789  -0.0435   0.1596   1.0000
  10.750   1.2919   0.02629   0.01895  -0.0416   0.1499   1.0000
  11.000   1.3024   0.02726   0.02003  -0.0400   0.1395   1.0000
  11.250   1.3111   0.02842   0.02123  -0.0383   0.1295   1.0000
  11.500   1.3174   0.02980   0.02258  -0.0366   0.1205   1.0000
  11.750   1.3250   0.03111   0.02395  -0.0351   0.1111   1.0000
  12.000   1.3325   0.03250   0.02541  -0.0337   0.1017   1.0000
  12.250   1.3364   0.03423   0.02710  -0.0322   0.0944   1.0000
  12.500   1.3437   0.03574   0.02871  -0.0310   0.0871   1.0000
  12.750   1.3475   0.03761   0.03060  -0.0298   0.0809   1.0000
  13.000   1.3537   0.03933   0.03241  -0.0288   0.0756   1.0000
  13.250   1.3535   0.04168   0.03471  -0.0276   0.0712   1.0000
  13.500   1.3607   0.04345   0.03666  -0.0268   0.0673   1.0000
  13.750   1.3641   0.04557   0.03887  -0.0261   0.0634   1.0000
  14.000   1.3624   0.04826   0.04155  -0.0254   0.0599   1.0000
  14.250   1.3678   0.05037   0.04386  -0.0250   0.0567   1.0000
  14.500   1.3701   0.05283   0.04645  -0.0248   0.0535   1.0000
  14.750   1.3676   0.05591   0.04955  -0.0247   0.0505   1.0000
  15.000   1.3676   0.05885   0.05263  -0.0247   0.0478   1.0000
  15.250   1.3678   0.06189   0.05583  -0.0250   0.0445   1.0000
  15.500   1.3634   0.06558   0.05959  -0.0257   0.0417   1.0000
  15.750   1.3574   0.06965   0.06378  -0.0265   0.0386   1.0000
  16.000   1.3525   0.07382   0.06811  -0.0276   0.0352   1.0000
  16.250   1.3394   0.07925   0.07355  -0.0295   0.0321   1.0000
  16.500   1.3307   0.08439   0.07890  -0.0313   0.0287   1.0000
  16.750   1.3193   0.09007   0.08467  -0.0336   0.0264   1.0000
  17.000   1.3060   0.09598   0.09061  -0.0359   0.0251   1.0000
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