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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 500,000
Max Cl/Cd: 112.11 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3512-il-500000.txt
Download as CSV file: xf-hq3512-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3601   0.03618   0.03318  -0.1089   0.9614   0.0147
  -8.250  -0.3514   0.03036   0.02697  -0.1118   0.9531   0.0141
  -8.000  -0.3443   0.02494   0.02090  -0.1121   0.9429   0.0139
  -7.750  -0.3294   0.02185   0.01734  -0.1114   0.9341   0.0139
  -7.500  -0.3083   0.01967   0.01478  -0.1110   0.9279   0.0141
  -7.250  -0.2870   0.01813   0.01296  -0.1103   0.9206   0.0143
  -7.000  -0.2624   0.01718   0.01180  -0.1098   0.9146   0.0146
  -6.750  -0.2412   0.01535   0.00976  -0.1091   0.9081   0.0154
  -6.500  -0.2166   0.01461   0.00894  -0.1087   0.9018   0.0161
  -6.250  -0.1912   0.01389   0.00810  -0.1083   0.8964   0.0167
  -6.000  -0.1667   0.01323   0.00735  -0.1078   0.8895   0.0176
  -5.750  -0.1407   0.01266   0.00666  -0.1074   0.8840   0.0187
  -5.500  -0.1162   0.01192   0.00585  -0.1069   0.8776   0.0202
  -5.250  -0.0899   0.01153   0.00544  -0.1066   0.8717   0.0228
  -5.000  -0.0635   0.01107   0.00491  -0.1064   0.8663   0.0277
  -4.750  -0.0369   0.01080   0.00467  -0.1062   0.8600   0.0373
  -4.500  -0.0091   0.01068   0.00449  -0.1061   0.8548   0.0439
  -4.250   0.0176   0.01042   0.00423  -0.1060   0.8488   0.0498
  -4.000   0.0451   0.01029   0.00403  -0.1059   0.8429   0.0537
  -3.750   0.0723   0.00999   0.00371  -0.1058   0.8378   0.0612
  -3.500   0.0996   0.00987   0.00356  -0.1057   0.8314   0.0672
  -3.250   0.1269   0.00954   0.00322  -0.1056   0.8259   0.0783
  -3.000   0.1541   0.00927   0.00298  -0.1055   0.8199   0.0958
  -2.750   0.1804   0.00875   0.00272  -0.1055   0.8136   0.1676
  -2.500   0.2052   0.00784   0.00247  -0.1056   0.8076   0.3754
  -2.250   0.2307   0.00740   0.00242  -0.1053   0.7999   0.5081
  -2.000   0.2578   0.00729   0.00238  -0.1050   0.7928   0.5622
  -1.750   0.2848   0.00724   0.00237  -0.1047   0.7846   0.5974
  -1.500   0.3124   0.00724   0.00234  -0.1045   0.7775   0.6207
  -1.250   0.3399   0.00724   0.00233  -0.1042   0.7701   0.6400
  -1.000   0.3677   0.00728   0.00233  -0.1041   0.7635   0.6591
  -0.750   0.3950   0.00730   0.00234  -0.1038   0.7558   0.6753
  -0.500   0.4221   0.00734   0.00239  -0.1034   0.7493   0.6959
  -0.250   0.4490   0.00737   0.00245  -0.1031   0.7418   0.7126
   0.000   0.4766   0.00741   0.00243  -0.1029   0.7345   0.7230
   0.250   0.5039   0.00742   0.00243  -0.1027   0.7259   0.7311
   0.500   0.5315   0.00744   0.00242  -0.1025   0.7179   0.7379
   0.750   0.5590   0.00746   0.00243  -0.1024   0.7102   0.7449
   1.000   0.5866   0.00749   0.00244  -0.1023   0.7025   0.7520
   1.250   0.6138   0.00752   0.00245  -0.1021   0.6942   0.7589
   1.500   0.6411   0.00754   0.00248  -0.1020   0.6850   0.7665
   1.750   0.6681   0.00758   0.00250  -0.1017   0.6767   0.7737
   2.000   0.6951   0.00762   0.00254  -0.1015   0.6671   0.7816
   2.250   0.7218   0.00765   0.00259  -0.1012   0.6569   0.7898
   2.500   0.7482   0.00770   0.00263  -0.1009   0.6458   0.7983
   2.750   0.7744   0.00777   0.00268  -0.1006   0.6341   0.8077
   3.000   0.8001   0.00780   0.00274  -0.1001   0.6211   0.8171
   3.250   0.8255   0.00787   0.00282  -0.0996   0.6060   0.8279
   3.500   0.8504   0.00794   0.00289  -0.0990   0.5888   0.8402
   3.750   0.8744   0.00801   0.00297  -0.0982   0.5684   0.8550
   4.000   0.8965   0.00811   0.00307  -0.0970   0.5447   0.8755
   4.250   0.9182   0.00819   0.00319  -0.0956   0.5160   0.9238
   4.500   0.9483   0.00852   0.00337  -0.0965   0.4775   1.0000
   4.750   0.9702   0.00895   0.00361  -0.0955   0.4411   1.0000
   5.000   0.9913   0.00942   0.00390  -0.0945   0.4047   1.0000
   5.250   1.0121   0.00991   0.00421  -0.0934   0.3700   1.0000
   5.500   1.0331   0.01037   0.00452  -0.0924   0.3392   1.0000
   5.750   1.0544   0.01082   0.00484  -0.0914   0.3152   1.0000
   6.000   1.0758   0.01125   0.00517  -0.0905   0.2976   1.0000
   6.250   1.0973   0.01165   0.00551  -0.0895   0.2835   1.0000
   6.500   1.1196   0.01200   0.00583  -0.0887   0.2727   1.0000
   6.750   1.1419   0.01233   0.00616  -0.0879   0.2641   1.0000
   7.250   1.1856   0.01302   0.00684  -0.0861   0.2476   1.0000
   7.500   1.2056   0.01343   0.00723  -0.0849   0.2402   1.0000
   7.750   1.2280   0.01369   0.00753  -0.0841   0.2310   1.0000
   8.000   1.2484   0.01403   0.00786  -0.0829   0.2205   1.0000
   8.250   1.2668   0.01440   0.00821  -0.0815   0.2090   1.0000
   8.500   1.2845   0.01478   0.00857  -0.0799   0.1966   1.0000
   8.750   1.3025   0.01517   0.00894  -0.0784   0.1842   1.0000
   9.000   1.3191   0.01563   0.00936  -0.0767   0.1698   1.0000
   9.250   1.3347   0.01616   0.00984  -0.0749   0.1541   1.0000
   9.500   1.3490   0.01677   0.01041  -0.0730   0.1380   1.0000
   9.750   1.3621   0.01746   0.01104  -0.0710   0.1226   1.0000
  10.000   1.3734   0.01829   0.01178  -0.0688   0.1061   1.0000
  10.250   1.3834   0.01921   0.01261  -0.0666   0.0901   1.0000
  10.500   1.3941   0.02012   0.01347  -0.0645   0.0762   1.0000
  10.750   1.4041   0.02111   0.01441  -0.0625   0.0635   1.0000
  11.000   1.4126   0.02223   0.01547  -0.0603   0.0504   1.0000
  11.250   1.4140   0.02388   0.01699  -0.0576   0.0300   1.0000
  11.500   1.4108   0.02597   0.01895  -0.0545   0.0146   1.0000
  11.750   1.4138   0.02767   0.02068  -0.0522   0.0110   1.0000
  12.000   1.4221   0.02899   0.02210  -0.0506   0.0100   1.0000
  12.250   1.4278   0.03056   0.02376  -0.0488   0.0090   1.0000
  12.500   1.4312   0.03239   0.02568  -0.0471   0.0084   1.0000
  12.750   1.4318   0.03452   0.02792  -0.0454   0.0080   1.0000
  13.000   1.4358   0.03641   0.02994  -0.0441   0.0077   1.0000
  13.250   1.4384   0.03850   0.03214  -0.0429   0.0075   1.0000
  13.500   1.4399   0.04077   0.03452  -0.0418   0.0072   1.0000
  13.750   1.4398   0.04330   0.03718  -0.0409   0.0070   1.0000
  14.000   1.4401   0.04588   0.03987  -0.0402   0.0068   1.0000
  14.250   1.4397   0.04864   0.04273  -0.0397   0.0066   1.0000
  14.500   1.4363   0.05189   0.04610  -0.0395   0.0064   1.0000
  14.750   1.4311   0.05552   0.04986  -0.0395   0.0063   1.0000
  15.000   1.4251   0.05940   0.05385  -0.0398   0.0062   1.0000
  15.250   1.4163   0.06388   0.05846  -0.0405   0.0060   1.0000
  15.500   1.4079   0.06852   0.06323  -0.0415   0.0060   1.0000
  15.750   1.3964   0.07382   0.06867  -0.0429   0.0059   1.0000
  16.000   1.3854   0.07928   0.07426  -0.0446   0.0059   1.0000
  16.250   1.3747   0.08491   0.08002  -0.0466   0.0058   1.0000
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