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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.69 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq309-il-1000000.txt
Download as CSV file: xf-hq309-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3679   0.08595   0.08440  -0.0360   1.0000   0.0072
  -8.250  -0.3732   0.08271   0.08120  -0.0359   1.0000   0.0073
  -8.000  -0.3748   0.07915   0.07767  -0.0373   0.9992   0.0073
  -7.750  -0.3593   0.07319   0.07171  -0.0451   0.9947   0.0073
  -7.500  -0.2754   0.04891   0.04752  -0.0608   0.9823   0.0086
  -7.250  -0.2683   0.03990   0.03845  -0.0759   0.9712   0.0086
  -7.000  -0.2584   0.03425   0.03267  -0.0822   0.9589   0.0089
  -6.750  -0.2514   0.02933   0.02760  -0.0852   0.9452   0.0092
  -6.500  -0.2418   0.02509   0.02319  -0.0867   0.9334   0.0097
  -6.250  -0.2295   0.02083   0.01871  -0.0877   0.9235   0.0104
  -4.750  -0.1030   0.01180   0.00709  -0.0931   0.8972   0.0078
  -4.500  -0.0769   0.01082   0.00595  -0.0927   0.8905   0.0076
  -4.250  -0.0512   0.00964   0.00459  -0.0922   0.8844   0.0078
  -4.000  -0.0251   0.00875   0.00356  -0.0919   0.8777   0.0087
  -3.750   0.0020   0.00838   0.00312  -0.0917   0.8718   0.0098
  -3.500   0.0293   0.00804   0.00271  -0.0916   0.8651   0.0107
  -3.250   0.0567   0.00777   0.00234  -0.0914   0.8589   0.0113
  -3.000   0.0843   0.00750   0.00200  -0.0913   0.8512   0.0127
  -2.750   0.1118   0.00718   0.00164  -0.0911   0.8436   0.0223
  -2.500   0.1394   0.00699   0.00149  -0.0910   0.8356   0.0442
  -2.250   0.1671   0.00686   0.00138  -0.0910   0.8288   0.0585
  -2.000   0.1948   0.00668   0.00126  -0.0910   0.8215   0.0864
  -1.750   0.2216   0.00611   0.00112  -0.0912   0.8148   0.2352
  -1.500   0.2472   0.00528   0.00102  -0.0913   0.8069   0.4902
  -1.250   0.2745   0.00512   0.00100  -0.0912   0.7974   0.5565
  -1.000   0.3018   0.00506   0.00097  -0.0910   0.7870   0.5953
  -0.750   0.3293   0.00504   0.00095  -0.0908   0.7770   0.6233
  -0.500   0.3570   0.00501   0.00094  -0.0907   0.7676   0.6472
  -0.250   0.3845   0.00499   0.00095  -0.0906   0.7587   0.6718
   0.000   0.4115   0.00498   0.00099  -0.0903   0.7488   0.7086
   0.250   0.4385   0.00499   0.00101  -0.0901   0.7365   0.7356
   0.500   0.4658   0.00502   0.00102  -0.0899   0.7237   0.7490
   0.750   0.4933   0.00504   0.00104  -0.0898   0.7118   0.7597
   1.000   0.5207   0.00508   0.00106  -0.0896   0.6997   0.7700
   1.250   0.5479   0.00512   0.00109  -0.0895   0.6865   0.7808
   1.500   0.5751   0.00517   0.00112  -0.0893   0.6729   0.7927
   1.750   0.6019   0.00523   0.00117  -0.0891   0.6577   0.8056
   2.000   0.6284   0.00530   0.00122  -0.0887   0.6406   0.8199
   2.250   0.6547   0.00536   0.00129  -0.0884   0.6215   0.8370
   2.500   0.6801   0.00542   0.00135  -0.0879   0.5994   0.8593
   2.750   0.7030   0.00542   0.00142  -0.0867   0.5737   0.9076
   3.000   0.7351   0.00554   0.00150  -0.0877   0.5408   1.0000
   3.250   0.7606   0.00582   0.00162  -0.0874   0.5038   1.0000
   3.500   0.7859   0.00612   0.00178  -0.0870   0.4666   1.0000
   3.750   0.8109   0.00646   0.00196  -0.0866   0.4274   1.0000
   4.000   0.8357   0.00681   0.00215  -0.0862   0.3899   1.0000
   4.250   0.8602   0.00720   0.00236  -0.0857   0.3477   1.0000
   4.500   0.8833   0.00772   0.00263  -0.0851   0.2931   1.0000
   4.750   0.9068   0.00821   0.00290  -0.0845   0.2476   1.0000
   5.000   0.9308   0.00864   0.00315  -0.0840   0.2123   1.0000
   5.250   0.9556   0.00900   0.00340  -0.0836   0.1873   1.0000
   5.500   0.9802   0.00935   0.00366  -0.0832   0.1642   1.0000
   5.750   1.0038   0.00980   0.00398  -0.0826   0.1354   1.0000
   6.000   1.0263   0.01038   0.00434  -0.0819   0.0988   1.0000
   6.250   1.0479   0.01103   0.00478  -0.0811   0.0634   1.0000
   6.500   1.0692   0.01172   0.00528  -0.0801   0.0343   1.0000
   6.750   1.0919   0.01226   0.00573  -0.0794   0.0196   1.0000
   7.000   1.1127   0.01300   0.00637  -0.0783   0.0053   1.0000
   7.250   1.1357   0.01349   0.00691  -0.0776   0.0043   1.0000
   7.500   1.1585   0.01399   0.00749  -0.0767   0.0038   1.0000
   7.750   1.1807   0.01456   0.00814  -0.0758   0.0036   1.0000
   8.000   1.2015   0.01526   0.00895  -0.0747   0.0034   1.0000
   8.250   1.2216   0.01601   0.00980  -0.0735   0.0034   1.0000
   8.500   1.2401   0.01688   0.01079  -0.0720   0.0034   1.0000
   8.750   1.2581   0.01775   0.01176  -0.0705   0.0034   1.0000
   9.000   1.2744   0.01875   0.01287  -0.0688   0.0034   1.0000
   9.250   1.2889   0.01985   0.01411  -0.0668   0.0034   1.0000
   9.500   1.3009   0.02112   0.01551  -0.0644   0.0033   1.0000
   9.750   1.3086   0.02271   0.01725  -0.0615   0.0033   1.0000
  10.000   1.3226   0.02344   0.01807  -0.0595   0.0031   1.0000
  10.250   1.3299   0.02468   0.01942  -0.0565   0.0031   1.0000
  10.500   1.3333   0.02633   0.02122  -0.0532   0.0031   1.0000
  10.750   1.3383   0.02787   0.02290  -0.0503   0.0031   1.0000
  11.000   1.3433   0.02943   0.02459  -0.0477   0.0031   1.0000
  11.250   1.3474   0.03108   0.02638  -0.0452   0.0031   1.0000
  11.500   1.3482   0.03314   0.02861  -0.0426   0.0031   1.0000
  11.750   1.3462   0.03557   0.03123  -0.0401   0.0031   1.0000
  12.000   1.3463   0.03772   0.03353  -0.0381   0.0031   1.0000
  12.250   1.3396   0.04080   0.03681  -0.0361   0.0031   1.0000
  12.500   1.3330   0.04394   0.04013  -0.0345   0.0031   1.0000
  12.750   1.3322   0.04637   0.04269  -0.0337   0.0030   1.0000
  13.000   1.3143   0.05132   0.04787  -0.0329   0.0031   1.0000
  13.250   1.3052   0.05527   0.05199  -0.0330   0.0031   1.0000
  13.500   1.2989   0.05908   0.05596  -0.0336   0.0030   1.0000
  13.750   1.2787   0.06535   0.06244  -0.0352   0.0030   1.0000
  14.000   1.2710   0.07008   0.06730  -0.0371   0.0030   1.0000
  14.250   1.2558   0.07652   0.07390  -0.0401   0.0030   1.0000
  14.500   1.2350   0.08467   0.08224  -0.0444   0.0030   1.0000
  14.750   1.2146   0.09349   0.09123  -0.0496   0.0030   1.0000
  15.000   1.1968   0.10242   0.10030  -0.0550   0.0030   1.0000
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