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HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/8 AIRFOIL (hq108-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.04 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq108-il-1000000.txt
Download as CSV file: xf-hq108-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/8 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6035   0.15564   0.15391   0.0192   1.0000   0.0048
 -13.000  -0.5982   0.15178   0.15005   0.0175   1.0000   0.0048
  -5.750  -0.5139   0.01651   0.01214  -0.0272   0.9984   0.0077
  -5.500  -0.4805   0.01493   0.01040  -0.0285   0.9956   0.0069
  -5.250  -0.4493   0.01251   0.00769  -0.0293   0.9921   0.0067
  -5.000  -0.4175   0.01105   0.00606  -0.0302   0.9878   0.0067
  -4.750  -0.3837   0.01011   0.00500  -0.0316   0.9843   0.0070
  -4.500  -0.3517   0.00884   0.00352  -0.0326   0.9788   0.0087
  -4.250  -0.3192   0.00839   0.00302  -0.0337   0.9716   0.0104
  -4.000  -0.2878   0.00806   0.00261  -0.0344   0.9626   0.0122
  -3.750  -0.2589   0.00758   0.00215  -0.0346   0.9513   0.0272
  -3.500  -0.2318   0.00730   0.00193  -0.0344   0.9379   0.0495
  -3.250  -0.2056   0.00709   0.00174  -0.0340   0.9240   0.0701
  -3.000  -0.1800   0.00677   0.00155  -0.0336   0.9105   0.1145
  -2.750  -0.1552   0.00627   0.00134  -0.0332   0.8970   0.2116
  -2.500  -0.1308   0.00568   0.00115  -0.0328   0.8839   0.3414
  -2.250  -0.1057   0.00522   0.00102  -0.0325   0.8719   0.4562
  -2.000  -0.0800   0.00492   0.00095  -0.0321   0.8610   0.5432
  -1.750  -0.0532   0.00479   0.00089  -0.0319   0.8502   0.5902
  -1.500  -0.0263   0.00472   0.00085  -0.0316   0.8379   0.6213
  -1.250   0.0006   0.00467   0.00082  -0.0313   0.8251   0.6543
  -1.000   0.0277   0.00463   0.00080  -0.0311   0.8130   0.6788
  -0.750   0.0548   0.00459   0.00079  -0.0308   0.8010   0.7031
  -0.500   0.0818   0.00457   0.00078  -0.0305   0.7888   0.7272
  -0.250   0.1092   0.00457   0.00077  -0.0303   0.7760   0.7426
   0.000   0.1366   0.00457   0.00076  -0.0301   0.7630   0.7559
   0.250   0.1639   0.00458   0.00077  -0.0300   0.7512   0.7713
   0.500   0.1912   0.00457   0.00078  -0.0298   0.7391   0.7877
   0.750   0.2185   0.00458   0.00080  -0.0295   0.7261   0.8041
   1.500   0.2995   0.00463   0.00086  -0.0288   0.6773   0.8462
   1.750   0.3259   0.00467   0.00090  -0.0284   0.6557   0.8622
   2.000   0.3517   0.00471   0.00094  -0.0279   0.6287   0.8824
   2.250   0.3763   0.00479   0.00099  -0.0270   0.5886   0.9098
   2.500   0.4040   0.00489   0.00106  -0.0269   0.5495   0.9527
   2.750   0.4422   0.00520   0.00117  -0.0294   0.4829   0.9854
   3.000   0.4732   0.00562   0.00132  -0.0304   0.4086   1.0000
   3.250   0.4977   0.00605   0.00148  -0.0300   0.3395   1.0000
   3.500   0.5226   0.00645   0.00166  -0.0296   0.2829   1.0000
   3.750   0.5476   0.00686   0.00186  -0.0292   0.2333   1.0000
   4.000   0.5732   0.00718   0.00207  -0.0290   0.1961   1.0000
   4.250   0.5984   0.00758   0.00228  -0.0287   0.1502   1.0000
   4.500   0.6228   0.00812   0.00257  -0.0283   0.0972   1.0000
   4.750   0.6480   0.00855   0.00285  -0.0280   0.0663   1.0000
   5.000   0.6734   0.00894   0.00315  -0.0276   0.0439   1.0000
   5.250   0.6987   0.00936   0.00346  -0.0273   0.0257   1.0000
   5.500   0.7230   0.01001   0.00407  -0.0267   0.0094   1.0000
   5.750   0.7486   0.01039   0.00449  -0.0263   0.0075   1.0000
   6.000   0.7711   0.01144   0.00570  -0.0253   0.0053   1.0000
   6.250   0.7955   0.01208   0.00642  -0.0247   0.0050   1.0000
   6.500   0.8187   0.01292   0.00738  -0.0238   0.0048   1.0000
   6.750   0.8409   0.01396   0.00855  -0.0229   0.0048   1.0000
   7.000   0.8620   0.01529   0.01004  -0.0217   0.0048   1.0000
   7.250   0.8822   0.01698   0.01192  -0.0205   0.0048   1.0000
   7.500   0.9010   0.01930   0.01451  -0.0190   0.0049   1.0000
   7.750   0.9197   0.02158   0.01705  -0.0177   0.0050   1.0000
   8.000   0.9407   0.02288   0.01852  -0.0168   0.0048   1.0000
   8.250   0.9592   0.02472   0.02059  -0.0156   0.0047   1.0000
   8.500   0.9712   0.02792   0.02414  -0.0138   0.0047   1.0000
   8.750   0.9761   0.03209   0.02873  -0.0114   0.0049   1.0000
   9.000   0.9587   0.04223   0.03965  -0.0064   0.0073   1.0000
   9.250   0.9605   0.04512   0.04275  -0.0047   0.0069   1.0000
   9.500   0.9484   0.04978   0.04766  -0.0023   0.0069   1.0000
   9.750   0.9381   0.05220   0.05020   0.0003   0.0067   1.0000
  10.000   0.9242   0.05463   0.05273   0.0021   0.0065   1.0000
  10.250   0.8936   0.06059   0.05887   0.0014   0.0067   1.0000
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