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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 500,000
Max Cl/Cd: 95.61 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3510-il-500000-n5.txt
Download as CSV file: xf-hq3510-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3390   0.11139   0.10906  -0.0386   1.0000   0.0086
 -10.250  -0.3368   0.10803   0.10573  -0.0393   1.0000   0.0086
 -10.000  -0.3358   0.10465   0.10238  -0.0398   1.0000   0.0086
  -9.500  -0.2180   0.08192   0.07980  -0.0538   0.9815   0.0078
  -9.250  -0.2129   0.07729   0.07517  -0.0563   0.9779   0.0074
  -9.000  -0.2078   0.07232   0.07021  -0.0593   0.9745   0.0070
  -8.750  -0.2049   0.06688   0.06477  -0.0625   0.9696   0.0067
  -8.500  -0.2034   0.06083   0.05872  -0.0664   0.9634   0.0064
  -8.250  -0.2112   0.05204   0.04995  -0.0721   0.9548   0.0058
  -8.000  -0.2112   0.04618   0.04409  -0.0770   0.9434   0.0059
  -7.750  -0.2672   0.05513   0.05293  -0.0889   0.9490   0.0054
  -7.250  -0.2528   0.03921   0.03650  -0.1034   0.9200   0.0053
  -7.000  -0.2587   0.02538   0.02173  -0.1062   0.9057   0.0054
  -6.750  -0.2441   0.02034   0.01599  -0.1065   0.8974   0.0058
  -6.500  -0.2207   0.01865   0.01400  -0.1065   0.8914   0.0061
  -6.250  -0.1964   0.01720   0.01229  -0.1064   0.8853   0.0064
  -6.000  -0.1713   0.01603   0.01087  -0.1062   0.8794   0.0067
  -5.750  -0.1453   0.01520   0.00985  -0.1061   0.8740   0.0073
  -5.500  -0.1193   0.01432   0.00879  -0.1060   0.8680   0.0078
  -5.250  -0.0931   0.01341   0.00765  -0.1057   0.8628   0.0081
  -5.000  -0.0669   0.01256   0.00664  -0.1055   0.8570   0.0083
  -4.750  -0.0403   0.01189   0.00583  -0.1053   0.8514   0.0085
  -4.500  -0.0141   0.01106   0.00486  -0.1051   0.8462   0.0090
  -4.250   0.0127   0.01051   0.00422  -0.1050   0.8402   0.0096
  -4.000   0.0400   0.01014   0.00376  -0.1049   0.8350   0.0102
  -3.750   0.0674   0.00985   0.00340  -0.1048   0.8292   0.0111
  -3.500   0.0950   0.00960   0.00308  -0.1048   0.8235   0.0122
  -3.250   0.1227   0.00937   0.00277  -0.1047   0.8180   0.0129
  -3.000   0.1505   0.00915   0.00250  -0.1047   0.8117   0.0146
  -2.750   0.1782   0.00893   0.00229  -0.1046   0.8060   0.0245
  -2.500   0.2059   0.00877   0.00213  -0.1046   0.7989   0.0368
  -2.250   0.2335   0.00865   0.00198  -0.1046   0.7916   0.0462
  -2.000   0.2610   0.00852   0.00185  -0.1045   0.7820   0.0613
  -1.750   0.2883   0.00841   0.00173  -0.1044   0.7712   0.0776
  -1.250   0.3421   0.00772   0.00148  -0.1045   0.7503   0.2655
  -1.000   0.3680   0.00705   0.00144  -0.1046   0.7404   0.4873
  -0.750   0.3949   0.00690   0.00146  -0.1044   0.7307   0.5628
  -0.500   0.4216   0.00684   0.00149  -0.1041   0.7201   0.6188
  -0.250   0.4481   0.00682   0.00155  -0.1037   0.7094   0.6664
   0.000   0.4749   0.00683   0.00158  -0.1034   0.6981   0.6948
   0.250   0.5019   0.00689   0.00158  -0.1032   0.6847   0.7048
   0.500   0.5290   0.00694   0.00159  -0.1030   0.6717   0.7125
   1.000   0.5833   0.00706   0.00164  -0.1027   0.6487   0.7294
   1.250   0.6101   0.00714   0.00168  -0.1024   0.6345   0.7380
   1.500   0.6367   0.00723   0.00173  -0.1022   0.6188   0.7473
   1.750   0.6631   0.00733   0.00179  -0.1019   0.6025   0.7566
   2.000   0.6891   0.00745   0.00187  -0.1015   0.5839   0.7666
   2.500   0.7395   0.00778   0.00206  -0.1005   0.5336   0.7889
   2.750   0.7639   0.00799   0.00219  -0.0998   0.5045   0.8013
   3.000   0.7874   0.00825   0.00236  -0.0991   0.4713   0.8151
   3.250   0.8107   0.00853   0.00254  -0.0983   0.4378   0.8316
   3.500   0.8333   0.00878   0.00273  -0.0973   0.4062   0.8533
   3.750   0.8538   0.00897   0.00292  -0.0958   0.3738   0.9020
   4.000   0.8835   0.00930   0.00316  -0.0966   0.3375   1.0000
   4.250   0.9074   0.00969   0.00340  -0.0960   0.3079   1.0000
   4.500   0.9317   0.01004   0.00365  -0.0956   0.2879   1.0000
   4.750   0.9563   0.01035   0.00389  -0.0951   0.2727   1.0000
   5.000   0.9810   0.01065   0.00415  -0.0947   0.2603   1.0000
   5.250   1.0057   0.01094   0.00443  -0.0943   0.2487   1.0000
   5.500   1.0301   0.01125   0.00470  -0.0938   0.2357   1.0000
   5.750   1.0537   0.01161   0.00499  -0.0933   0.2187   1.0000
   6.000   1.0772   0.01198   0.00527  -0.0927   0.1972   1.0000
   6.250   1.1000   0.01239   0.00561  -0.0920   0.1763   1.0000
   6.500   1.1224   0.01283   0.00595  -0.0913   0.1535   1.0000
   6.750   1.1435   0.01337   0.00637  -0.0904   0.1275   1.0000
   7.000   1.1611   0.01420   0.00695  -0.0890   0.0893   1.0000
   7.250   1.1770   0.01518   0.00767  -0.0873   0.0516   1.0000
   7.500   1.1920   0.01622   0.00850  -0.0855   0.0201   1.0000
   7.750   1.2083   0.01713   0.00935  -0.0838   0.0054   1.0000
   8.000   1.2280   0.01769   0.00996  -0.0826   0.0045   1.0000
   8.250   1.2471   0.01828   0.01061  -0.0813   0.0041   1.0000
   8.500   1.2652   0.01889   0.01131  -0.0799   0.0037   1.0000
   8.750   1.2811   0.01956   0.01208  -0.0781   0.0034   1.0000
   9.000   1.2951   0.02034   0.01297  -0.0759   0.0032   1.0000
   9.250   1.3089   0.02111   0.01383  -0.0739   0.0032   1.0000
   9.500   1.3218   0.02194   0.01476  -0.0718   0.0031   1.0000
   9.750   1.3338   0.02283   0.01575  -0.0696   0.0030   1.0000
  10.000   1.3451   0.02377   0.01682  -0.0675   0.0029   1.0000
  10.250   1.3559   0.02475   0.01789  -0.0654   0.0027   1.0000
  10.500   1.3650   0.02586   0.01911  -0.0632   0.0026   1.0000
  10.750   1.3731   0.02709   0.02044  -0.0611   0.0025   1.0000
  11.000   1.3800   0.02843   0.02189  -0.0590   0.0023   1.0000
  11.250   1.3854   0.02993   0.02351  -0.0568   0.0023   1.0000
  11.500   1.3902   0.03153   0.02522  -0.0549   0.0022   1.0000
  11.750   1.3933   0.03335   0.02715  -0.0530   0.0022   1.0000
  12.000   1.3953   0.03533   0.02926  -0.0512   0.0021   1.0000
  12.250   1.3965   0.03747   0.03152  -0.0496   0.0020   1.0000
  12.500   1.3962   0.03986   0.03403  -0.0482   0.0020   1.0000
  12.750   1.3947   0.04249   0.03679  -0.0470   0.0020   1.0000
  13.000   1.3896   0.04564   0.04007  -0.0461   0.0019   1.0000
  13.250   1.3843   0.04899   0.04359  -0.0454   0.0018   1.0000
  13.500   1.3779   0.05265   0.04739  -0.0451   0.0018   1.0000
  13.750   1.3714   0.05651   0.05140  -0.0452   0.0018   1.0000
  14.000   1.3632   0.06084   0.05588  -0.0456   0.0018   1.0000
  14.250   1.3539   0.06558   0.06077  -0.0465   0.0017   1.0000
  14.500   1.3354   0.07195   0.06734  -0.0479   0.0017   1.0000
  14.750   1.3278   0.07700   0.07254  -0.0496   0.0017   1.0000
  15.000   1.3193   0.08245   0.07815  -0.0517   0.0017   1.0000
  15.250   1.3099   0.08826   0.08411  -0.0541   0.0017   1.0000
  15.500   1.3028   0.09403   0.09004  -0.0569   0.0016   1.0000
  15.750   1.2925   0.10050   0.09667  -0.0601   0.0016   1.0000
  16.000   1.2814   0.10727   0.10359  -0.0635   0.0016   1.0000
  16.250   1.2716   0.11411   0.11057  -0.0672   0.0016   1.0000
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