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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.42 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1585-il-1000000-n5.txt
Download as CSV file: xf-hq1585-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8.5 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.9523   0.04030   0.03831  -0.0504   1.0000   0.0027
 -12.000  -0.9742   0.03623   0.03403  -0.0498   1.0000   0.0026
 -11.750  -0.9767   0.03293   0.03049  -0.0493   1.0000   0.0027
 -11.500  -0.9788   0.02907   0.02628  -0.0487   1.0000   0.0028
 -11.250  -0.9689   0.02664   0.02360  -0.0480   1.0000   0.0028
 -11.000  -0.9556   0.02454   0.02125  -0.0474   1.0000   0.0029
 -10.750  -0.9390   0.02287   0.01937  -0.0469   1.0000   0.0030
 -10.500  -0.9200   0.02156   0.01789  -0.0464   1.0000   0.0031
 -10.250  -0.9005   0.02023   0.01637  -0.0458   1.0000   0.0032
 -10.000  -0.8802   0.01900   0.01496  -0.0453   1.0000   0.0032
  -9.750  -0.8585   0.01804   0.01384  -0.0448   1.0000   0.0033
  -9.500  -0.8365   0.01711   0.01276  -0.0443   1.0000   0.0034
  -9.250  -0.8137   0.01637   0.01192  -0.0438   1.0000   0.0034
  -9.000  -0.7928   0.01517   0.01053  -0.0431   1.0000   0.0037
  -8.750  -0.7707   0.01430   0.00955  -0.0424   1.0000   0.0041
  -8.500  -0.7400   0.01365   0.00882  -0.0434   0.9934   0.0044
  -8.250  -0.7079   0.01309   0.00820  -0.0448   0.9857   0.0047
  -8.000  -0.6746   0.01262   0.00765  -0.0463   0.9757   0.0052
  -7.750  -0.6409   0.01216   0.00712  -0.0478   0.9635   0.0057
  -7.500  -0.6101   0.01175   0.00662  -0.0487   0.9475   0.0060
  -7.250  -0.5835   0.01120   0.00597  -0.0486   0.9307   0.0070
  -7.000  -0.5574   0.01093   0.00566  -0.0483   0.9162   0.0079
  -6.750  -0.5314   0.01069   0.00534  -0.0480   0.9032   0.0088
  -6.500  -0.5052   0.01046   0.00502  -0.0477   0.8912   0.0096
  -6.250  -0.4787   0.01029   0.00478  -0.0475   0.8796   0.0100
  -6.000  -0.4527   0.00989   0.00430  -0.0472   0.8683   0.0113
  -5.750  -0.4260   0.00970   0.00409  -0.0470   0.8578   0.0125
  -5.500  -0.3991   0.00950   0.00382  -0.0469   0.8488   0.0135
  -5.250  -0.3722   0.00928   0.00354  -0.0467   0.8405   0.0144
  -5.000  -0.3450   0.00910   0.00330  -0.0466   0.8335   0.0152
  -4.750  -0.3176   0.00897   0.00312  -0.0465   0.8270   0.0157
  -4.500  -0.2905   0.00866   0.00273  -0.0464   0.8215   0.0172
  -4.250  -0.2631   0.00842   0.00245  -0.0463   0.8160   0.0191
  -3.750  -0.2078   0.00808   0.00204  -0.0462   0.8065   0.0216
  -3.500  -0.1800   0.00794   0.00185  -0.0462   0.8018   0.0231
  -3.250  -0.1522   0.00781   0.00169  -0.0461   0.7973   0.0263
  -3.000  -0.1244   0.00764   0.00155  -0.0462   0.7926   0.0340
  -2.750  -0.0966   0.00748   0.00142  -0.0461   0.7867   0.0476
  -2.500  -0.0690   0.00733   0.00129  -0.0461   0.7794   0.0640
  -2.250  -0.0417   0.00708   0.00114  -0.0461   0.7707   0.1042
  -2.000  -0.0144   0.00680   0.00103  -0.0461   0.7623   0.1593
  -1.750   0.0130   0.00657   0.00093  -0.0461   0.7531   0.2082
  -1.500   0.0403   0.00633   0.00084  -0.0461   0.7422   0.2670
  -1.250   0.0671   0.00594   0.00074  -0.0461   0.7306   0.3646
  -1.000   0.0936   0.00553   0.00068  -0.0460   0.7167   0.4842
  -0.750   0.1209   0.00541   0.00064  -0.0459   0.7008   0.5333
  -0.500   0.1484   0.00535   0.00062  -0.0459   0.6853   0.5664
  -0.250   0.1759   0.00527   0.00062  -0.0458   0.6722   0.6059
   0.000   0.2035   0.00526   0.00062  -0.0457   0.6579   0.6310
   0.250   0.2311   0.00528   0.00064  -0.0456   0.6406   0.6495
   0.500   0.2587   0.00532   0.00066  -0.0455   0.6229   0.6670
   0.750   0.2862   0.00537   0.00070  -0.0453   0.6040   0.6854
   1.000   0.3124   0.00557   0.00077  -0.0450   0.5544   0.7072
   1.250   0.3375   0.00595   0.00087  -0.0446   0.4711   0.7235
   1.500   0.3631   0.00632   0.00100  -0.0443   0.4035   0.7361
   1.750   0.3892   0.00663   0.00112  -0.0440   0.3464   0.7475
   2.000   0.4154   0.00693   0.00125  -0.0438   0.2989   0.7576
   2.250   0.4423   0.00713   0.00136  -0.0437   0.2689   0.7672
   2.500   0.4690   0.00734   0.00148  -0.0436   0.2385   0.7750
   3.000   0.5221   0.00784   0.00176  -0.0432   0.1767   0.7882
   3.250   0.5479   0.00821   0.00195  -0.0430   0.1298   0.7950
   3.500   0.5738   0.00852   0.00215  -0.0428   0.0976   0.8019
   4.000   0.6251   0.00921   0.00264  -0.0421   0.0367   0.8187
   4.250   0.6517   0.00934   0.00281  -0.0419   0.0345   0.8296
   4.500   0.6778   0.00949   0.00301  -0.0416   0.0318   0.8449
   4.750   0.7028   0.00962   0.00323  -0.0410   0.0291   0.8726
   5.000   0.7290   0.00963   0.00346  -0.0406   0.0276   0.9540
   5.250   0.7609   0.00987   0.00373  -0.0416   0.0257   1.0000
   5.500   0.7876   0.01009   0.00396  -0.0415   0.0245   1.0000
   5.750   0.8144   0.01026   0.00414  -0.0414   0.0235   1.0000
   6.000   0.8410   0.01047   0.00436  -0.0412   0.0217   1.0000
   6.250   0.8669   0.01078   0.00462  -0.0410   0.0169   1.0000
   6.500   0.8920   0.01120   0.00498  -0.0407   0.0092   1.0000
   6.750   0.9175   0.01157   0.00535  -0.0404   0.0065   1.0000
   7.000   0.9429   0.01194   0.00576  -0.0400   0.0057   1.0000
   7.250   0.9678   0.01237   0.00623  -0.0396   0.0050   1.0000
   7.500   0.9923   0.01285   0.00677  -0.0392   0.0043   1.0000
   7.750   1.0163   0.01343   0.00742  -0.0386   0.0039   1.0000
   8.000   1.0410   0.01384   0.00788  -0.0382   0.0038   1.0000
   8.250   1.0652   0.01431   0.00843  -0.0378   0.0036   1.0000
   8.500   1.0889   0.01483   0.00902  -0.0373   0.0035   1.0000
   8.750   1.1121   0.01542   0.00968  -0.0367   0.0033   1.0000
   9.000   1.1350   0.01602   0.01035  -0.0360   0.0031   1.0000
   9.250   1.1576   0.01664   0.01104  -0.0354   0.0029   1.0000
   9.500   1.1799   0.01726   0.01172  -0.0348   0.0027   1.0000
   9.750   1.2017   0.01790   0.01242  -0.0341   0.0025   1.0000
  10.000   1.2222   0.01870   0.01332  -0.0332   0.0024   1.0000
  10.250   1.2403   0.01979   0.01454  -0.0321   0.0022   1.0000
  10.500   1.2553   0.02119   0.01610  -0.0306   0.0021   1.0000
  10.750   1.2717   0.02233   0.01738  -0.0292   0.0021   1.0000
  11.000   1.2886   0.02331   0.01847  -0.0280   0.0020   1.0000
  11.250   1.3034   0.02444   0.01973  -0.0266   0.0020   1.0000
  11.500   1.3180   0.02549   0.02090  -0.0251   0.0020   1.0000
  11.750   1.3291   0.02676   0.02232  -0.0233   0.0019   1.0000
  12.000   1.3374   0.02796   0.02365  -0.0211   0.0019   1.0000
  12.250   1.3410   0.02926   0.02507  -0.0182   0.0019   1.0000
  12.500   1.3414   0.03081   0.02677  -0.0154   0.0019   1.0000
  12.750   1.3425   0.03242   0.02851  -0.0132   0.0019   1.0000
  13.000   1.3390   0.03457   0.03082  -0.0111   0.0018   1.0000
  13.250   1.3350   0.03696   0.03338  -0.0096   0.0018   1.0000
  13.500   1.3311   0.03955   0.03612  -0.0087   0.0018   1.0000
  13.750   1.3240   0.04272   0.03944  -0.0083   0.0018   1.0000
  14.000   1.3181   0.04603   0.04289  -0.0085   0.0018   1.0000
  14.250   1.3018   0.05106   0.04811  -0.0097   0.0017   1.0000
  14.500   1.2804   0.05755   0.05479  -0.0125   0.0018   1.0000
  14.750   1.2767   0.06188   0.05922  -0.0148   0.0017   1.0000
  15.000   1.2555   0.06998   0.06750  -0.0198   0.0017   1.0000
  15.250   1.2244   0.08125   0.07896  -0.0270   0.0018   1.0000
  15.500   1.1850   0.09522   0.09313  -0.0356   0.0018   1.0000
  15.750   1.1463   0.10928   0.10732  -0.0438   0.0018   1.0000
  16.000   1.1090   0.12330   0.12146  -0.0516   0.0019   1.0000
  16.250   1.0647   0.13993   0.13821  -0.0608   0.0019   1.0000
  16.500   1.0163   0.15935   0.15775  -0.0713   0.0020   1.0000
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