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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 500,000
Max Cl/Cd: 99.5 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq308-il-500000-n5.txt
Download as CSV file: xf-hq308-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/8 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3629   0.08886   0.08666  -0.0328   1.0000   0.0053
  -8.000  -0.3632   0.08604   0.08387  -0.0331   1.0000   0.0053
  -7.750  -0.3664   0.08354   0.08142  -0.0326   1.0000   0.0053
  -7.500  -0.3579   0.07927   0.07717  -0.0365   0.9947   0.0053
  -7.250  -0.3427   0.07426   0.07218  -0.0429   0.9872   0.0053
  -7.000  -0.3275   0.06820   0.06612  -0.0514   0.9800   0.0049
  -6.750  -0.3014   0.06084   0.05868  -0.0643   0.9744   0.0045
  -6.500  -0.2768   0.05434   0.05209  -0.0740   0.9658   0.0043
  -6.250  -0.2502   0.04790   0.04549  -0.0822   0.9582   0.0041
  -6.000  -0.2255   0.04212   0.03951  -0.0876   0.9491   0.0038
  -5.750  -0.2022   0.03666   0.03378  -0.0909   0.9397   0.0037
  -5.500  -0.1779   0.03150   0.02829  -0.0930   0.9314   0.0036
  -5.250  -0.1536   0.02639   0.02277  -0.0939   0.9231   0.0035
  -5.000  -0.1286   0.02124   0.01712  -0.0940   0.9156   0.0036
  -4.750  -0.1026   0.01725   0.01258  -0.0937   0.9089   0.0041
  -4.500  -0.0761   0.01508   0.01001  -0.0934   0.9023   0.0045
  -4.250  -0.0491   0.01396   0.00863  -0.0932   0.8960   0.0050
  -4.000  -0.0228   0.01253   0.00693  -0.0930   0.8897   0.0063
  -3.750   0.0039   0.01168   0.00595  -0.0928   0.8832   0.0069
  -3.500   0.0308   0.01075   0.00485  -0.0924   0.8770   0.0071
  -3.250   0.0577   0.01004   0.00399  -0.0922   0.8703   0.0077
  -3.000   0.0850   0.00949   0.00332  -0.0920   0.8641   0.0086
  -2.750   0.1125   0.00909   0.00283  -0.0918   0.8573   0.0097
  -2.500   0.1400   0.00880   0.00243  -0.0917   0.8509   0.0113
  -2.250   0.1677   0.00853   0.00204  -0.0916   0.8436   0.0121
  -2.000   0.1954   0.00836   0.00178  -0.0914   0.8362   0.0144
  -1.750   0.2228   0.00817   0.00158  -0.0913   0.8269   0.0300
  -1.500   0.2502   0.00798   0.00145  -0.0912   0.8166   0.0612
  -1.250   0.2776   0.00783   0.00133  -0.0911   0.8073   0.0918
  -0.750   0.3296   0.00639   0.00123  -0.0914   0.7889   0.5673
  -0.500   0.3556   0.00624   0.00126  -0.0909   0.7761   0.6502
  -0.250   0.3813   0.00616   0.00130  -0.0903   0.7621   0.7106
   0.000   0.4078   0.00615   0.00130  -0.0899   0.7501   0.7422
   0.250   0.4350   0.00617   0.00129  -0.0897   0.7388   0.7534
   0.500   0.4621   0.00620   0.00129  -0.0895   0.7266   0.7647
   0.750   0.4887   0.00624   0.00129  -0.0892   0.7102   0.7769
   1.000   0.5149   0.00631   0.00130  -0.0887   0.6892   0.7901
   1.250   0.5410   0.00638   0.00132  -0.0883   0.6684   0.8046
   1.500   0.5669   0.00644   0.00137  -0.0878   0.6505   0.8216
   1.750   0.5925   0.00649   0.00142  -0.0873   0.6312   0.8423
   2.000   0.6167   0.00652   0.00147  -0.0864   0.6089   0.8733
   2.250   0.6479   0.00653   0.00150  -0.0871   0.5794   1.0000
   2.500   0.6736   0.00677   0.00162  -0.0868   0.5464   1.0000
   2.750   0.6987   0.00707   0.00175  -0.0863   0.5074   1.0000
   3.000   0.7236   0.00741   0.00191  -0.0859   0.4665   1.0000
   3.250   0.7483   0.00778   0.00210  -0.0854   0.4260   1.0000
   3.500   0.7731   0.00814   0.00231  -0.0850   0.3891   1.0000
   3.750   0.7973   0.00858   0.00258  -0.0845   0.3433   1.0000
   4.000   0.8208   0.00910   0.00285  -0.0840   0.2918   1.0000
   4.250   0.8440   0.00967   0.00316  -0.0834   0.2383   1.0000
   4.500   0.8650   0.01050   0.00356  -0.0826   0.1621   1.0000
   4.750   0.8884   0.01105   0.00390  -0.0821   0.1218   1.0000
   5.000   0.9119   0.01158   0.00426  -0.0815   0.0879   1.0000
   5.250   0.9354   0.01211   0.00469  -0.0810   0.0600   1.0000
   5.500   0.9590   0.01263   0.00512  -0.0804   0.0389   1.0000
   5.750   0.9808   0.01338   0.00570  -0.0796   0.0119   1.0000
   6.000   1.0042   0.01393   0.00623  -0.0789   0.0042   1.0000
   6.250   1.0284   0.01437   0.00674  -0.0784   0.0036   1.0000
   6.500   1.0520   0.01488   0.00735  -0.0777   0.0032   1.0000
   6.750   1.0752   0.01543   0.00799  -0.0770   0.0030   1.0000
   7.000   1.0978   0.01604   0.00876  -0.0762   0.0028   1.0000
   7.250   1.1198   0.01673   0.00956  -0.0752   0.0027   1.0000
   7.500   1.1409   0.01751   0.01046  -0.0742   0.0027   1.0000
   7.750   1.1609   0.01839   0.01147  -0.0730   0.0026   1.0000
   8.000   1.1801   0.01934   0.01254  -0.0717   0.0026   1.0000
   8.250   1.1977   0.02044   0.01377  -0.0702   0.0025   1.0000
   8.500   1.2133   0.02173   0.01520  -0.0686   0.0023   1.0000
   8.750   1.2232   0.02374   0.01740  -0.0661   0.0020   1.0000
   9.000   1.2366   0.02533   0.01916  -0.0641   0.0018   1.0000
   9.250   1.2535   0.02630   0.02027  -0.0627   0.0017   1.0000
   9.500   1.2663   0.02778   0.02193  -0.0608   0.0017   1.0000
   9.750   1.2775   0.02926   0.02364  -0.0587   0.0016   1.0000
  10.000   1.2850   0.03088   0.02546  -0.0560   0.0015   1.0000
  10.250   1.2898   0.03265   0.02744  -0.0531   0.0015   1.0000
  10.500   1.2931   0.03449   0.02949  -0.0503   0.0014   1.0000
  10.750   1.2933   0.03665   0.03187  -0.0475   0.0013   1.0000
  11.000   1.2905   0.03913   0.03458  -0.0448   0.0013   1.0000
  11.250   1.2865   0.04175   0.03743  -0.0425   0.0013   1.0000
  11.500   1.2794   0.04483   0.04074  -0.0405   0.0012   1.0000
  11.750   1.2709   0.04819   0.04433  -0.0391   0.0012   1.0000
  12.000   1.2600   0.05209   0.04845  -0.0384   0.0012   1.0000
  12.250   1.2479   0.05644   0.05301  -0.0384   0.0011   1.0000
  12.500   1.2329   0.06163   0.05841  -0.0394   0.0011   1.0000
  12.750   1.2160   0.06768   0.06467  -0.0416   0.0011   1.0000
  13.000   1.1999   0.07425   0.07142  -0.0447   0.0011   1.0000
  13.250   1.1830   0.08176   0.07911  -0.0490   0.0011   1.0000
  13.500   1.1641   0.09067   0.08820  -0.0545   0.0012   1.0000
  13.750   1.1454   0.10046   0.09815  -0.0607   0.0012   1.0000
  14.000   1.1259   0.11120   0.10902  -0.0673   0.0012   1.0000
  14.250   1.1076   0.12202   0.11995  -0.0737   0.0013   1.0000
  14.500   1.0889   0.13332   0.13134  -0.0800   0.0013   1.0000
  14.750   1.0689   0.14538   0.14347  -0.0864   0.0014   1.0000
  15.000   1.0488   0.15814   0.15627  -0.0929   0.0015   1.0000
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