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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.62 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq359-il-1000000.txt
Download as CSV file: xf-hq359-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2350   0.08096   0.07949  -0.0476   0.9934   0.0070
  -8.750  -0.2285   0.07626   0.07479  -0.0503   0.9906   0.0070
  -8.500  -0.2320   0.06921   0.06776  -0.0538   0.9877   0.0073
  -8.250  -0.2247   0.06458   0.06314  -0.0571   0.9851   0.0075
  -8.000  -0.2150   0.05992   0.05848  -0.0611   0.9830   0.0077
  -7.750  -0.2037   0.05618   0.05473  -0.0644   0.9785   0.0080
  -7.500  -0.1912   0.05189   0.05044  -0.0690   0.9732   0.0083
  -7.250  -0.1820   0.04687   0.04541  -0.0747   0.9638   0.0085
  -7.000  -0.1780   0.04191   0.04043  -0.0809   0.9493   0.0087
  -6.750  -0.1765   0.03622   0.03465  -0.0883   0.9344   0.0087
  -6.500  -0.1709   0.03135   0.02966  -0.0922   0.9230   0.0088
  -6.250  -0.1611   0.02700   0.02515  -0.0949   0.9139   0.0091
  -6.000  -0.1481   0.02274   0.02072  -0.0969   0.9053   0.0093
  -5.750  -0.1315   0.01877   0.01654  -0.0985   0.8985   0.0099
  -5.500  -0.1106   0.01546   0.01301  -0.0994   0.8921   0.0108
  -5.250  -0.0855   0.01376   0.01113  -0.0994   0.8868   0.0115
  -5.000  -0.0631   0.01104   0.00812  -0.1000   0.8808   0.0116
  -4.750  -0.0444   0.00598   0.00241  -0.1018   0.8760   0.0127
  -4.250   0.0153   0.01111   0.00638  -0.1068   0.8784   0.0076
  -4.000   0.0417   0.00986   0.00493  -0.1065   0.8732   0.0079
  -3.750   0.0687   0.00924   0.00424  -0.1063   0.8673   0.0089
  -3.500   0.0959   0.00879   0.00370  -0.1062   0.8617   0.0097
  -3.250   0.1233   0.00832   0.00315  -0.1061   0.8558   0.0102
  -3.000   0.1507   0.00798   0.00272  -0.1059   0.8488   0.0109
  -2.750   0.1782   0.00771   0.00238  -0.1058   0.8405   0.0114
  -2.500   0.2056   0.00740   0.00195  -0.1055   0.8314   0.0116
  -2.250   0.2334   0.00707   0.00149  -0.1053   0.8222   0.0142
  -2.000   0.2611   0.00681   0.00131  -0.1053   0.8142   0.0436
  -1.750   0.2888   0.00668   0.00121  -0.1053   0.8065   0.0670
  -1.500   0.3165   0.00642   0.00111  -0.1054   0.7982   0.1281
  -1.250   0.3428   0.00555   0.00099  -0.1057   0.7899   0.4064
  -1.000   0.3694   0.00516   0.00100  -0.1057   0.7812   0.5630
  -0.750   0.3970   0.00509   0.00100  -0.1056   0.7727   0.6079
  -0.500   0.4244   0.00508   0.00099  -0.1054   0.7631   0.6378
  -0.250   0.4517   0.00508   0.00100  -0.1053   0.7521   0.6666
   0.000   0.4790   0.00506   0.00102  -0.1051   0.7420   0.6961
   0.250   0.5062   0.00506   0.00106  -0.1049   0.7326   0.7257
   0.500   0.5333   0.00509   0.00108  -0.1046   0.7220   0.7465
   1.000   0.5879   0.00517   0.00112  -0.1044   0.6983   0.7672
   1.250   0.6151   0.00522   0.00115  -0.1042   0.6854   0.7782
   1.750   0.6687   0.00535   0.00123  -0.1037   0.6560   0.8027
   2.000   0.6952   0.00541   0.00129  -0.1034   0.6389   0.8174
   2.250   0.7211   0.00548   0.00136  -0.1030   0.6188   0.8356
   2.500   0.7459   0.00555   0.00143  -0.1024   0.5955   0.8621
   2.750   0.7734   0.00550   0.00149  -0.1023   0.5649   1.0000
   3.000   0.7986   0.00577   0.00161  -0.1019   0.5286   1.0000
   3.250   0.8233   0.00611   0.00175  -0.1014   0.4865   1.0000
   3.500   0.8476   0.00648   0.00195  -0.1009   0.4433   1.0000
   3.750   0.8720   0.00686   0.00214  -0.1004   0.4027   1.0000
   4.000   0.8963   0.00724   0.00235  -0.0999   0.3637   1.0000
   4.250   0.9202   0.00767   0.00258  -0.0993   0.3199   1.0000
   4.500   0.9442   0.00808   0.00284  -0.0988   0.2860   1.0000
   4.750   0.9691   0.00840   0.00306  -0.0984   0.2645   1.0000
   5.000   0.9935   0.00875   0.00330  -0.0979   0.2421   1.0000
   5.250   1.0187   0.00902   0.00351  -0.0976   0.2245   1.0000
   5.500   1.0439   0.00930   0.00373  -0.0973   0.2081   1.0000
   5.750   1.0676   0.00970   0.00401  -0.0967   0.1789   1.0000
   6.000   1.0891   0.01031   0.00437  -0.0959   0.1360   1.0000
   6.250   1.1091   0.01108   0.00486  -0.0948   0.0897   1.0000
   6.500   1.1266   0.01210   0.00556  -0.0933   0.0384   1.0000
   6.750   1.1446   0.01311   0.00636  -0.0917   0.0061   1.0000
   7.000   1.1674   0.01360   0.00688  -0.0909   0.0047   1.0000
   7.250   1.1899   0.01410   0.00748  -0.0900   0.0042   1.0000
   7.500   1.2116   0.01469   0.00816  -0.0890   0.0039   1.0000
   7.750   1.2320   0.01539   0.00897  -0.0878   0.0038   1.0000
   8.000   1.2513   0.01617   0.00986  -0.0864   0.0038   1.0000
   8.250   1.2681   0.01715   0.01097  -0.0846   0.0037   1.0000
   8.500   1.2830   0.01825   0.01219  -0.0826   0.0036   1.0000
   8.750   1.3018   0.01890   0.01291  -0.0812   0.0035   1.0000
   9.000   1.3177   0.01976   0.01386  -0.0795   0.0034   1.0000
   9.250   1.3308   0.02081   0.01501  -0.0772   0.0034   1.0000
   9.500   1.3397   0.02193   0.01626  -0.0743   0.0034   1.0000
   9.750   1.3488   0.02297   0.01740  -0.0714   0.0033   1.0000
  10.000   1.3555   0.02424   0.01878  -0.0684   0.0033   1.0000
  10.250   1.3619   0.02560   0.02026  -0.0655   0.0032   1.0000
  10.500   1.3706   0.02677   0.02153  -0.0631   0.0031   1.0000
  10.750   1.3750   0.02844   0.02334  -0.0603   0.0031   1.0000
  11.000   1.3807   0.03000   0.02502  -0.0578   0.0029   1.0000
  11.250   1.3832   0.03201   0.02718  -0.0552   0.0029   1.0000
  11.500   1.3871   0.03378   0.02907  -0.0531   0.0027   1.0000
  11.750   1.3899   0.03564   0.03106  -0.0511   0.0026   1.0000
  12.000   1.3880   0.03827   0.03385  -0.0489   0.0025   1.0000
  12.250   1.3868   0.04076   0.03648  -0.0471   0.0025   1.0000
  12.500   1.3780   0.04449   0.04045  -0.0452   0.0025   1.0000
  12.750   1.3642   0.04907   0.04530  -0.0435   0.0026   1.0000
  13.000   1.3437   0.05480   0.05134  -0.0425   0.0028   1.0000
  13.250   1.3215   0.06098   0.05780  -0.0426   0.0029   1.0000
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