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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 50,000
Max Cl/Cd: 37.91 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-50000-n5.txt
Download as CSV file: xf-hq2090sm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ-2.0/9  9.0%   smoothed                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4616   0.09506   0.08809  -0.0281   1.0000   0.0444
  -8.750  -0.4624   0.09081   0.08392  -0.0301   1.0000   0.0435
  -8.500  -0.4646   0.08647   0.07967  -0.0325   1.0000   0.0425
  -8.250  -0.4693   0.08188   0.07517  -0.0353   1.0000   0.0417
  -8.000  -0.4768   0.07669   0.07008  -0.0393   1.0000   0.0407
  -7.750  -0.4832   0.07151   0.06491  -0.0428   1.0000   0.0398
  -7.500  -0.4894   0.06643   0.05976  -0.0454   1.0000   0.0389
  -7.250  -0.4917   0.06207   0.05530  -0.0466   1.0000   0.0388
  -7.000  -0.4909   0.05814   0.05122  -0.0471   1.0000   0.0390
  -6.750  -0.4868   0.05477   0.04770  -0.0470   1.0000   0.0401
  -6.500  -0.4809   0.05137   0.04408  -0.0467   1.0000   0.0415
  -6.250  -0.4729   0.04791   0.04033  -0.0464   1.0000   0.0430
  -6.000  -0.4625   0.04439   0.03642  -0.0458   1.0000   0.0443
  -5.750  -0.4493   0.04092   0.03251  -0.0451   1.0000   0.0450
  -5.500  -0.4335   0.03762   0.02869  -0.0442   1.0000   0.0460
  -5.250  -0.4151   0.03456   0.02506  -0.0432   1.0000   0.0476
  -5.000  -0.3956   0.03209   0.02211  -0.0422   1.0000   0.0512
  -4.750  -0.3768   0.03047   0.02034  -0.0412   1.0000   0.0574
  -4.500  -0.3547   0.02844   0.01783  -0.0399   1.0000   0.0617
  -4.250  -0.3344   0.02692   0.01619  -0.0387   1.0000   0.0693
  -4.000  -0.3136   0.02561   0.01471  -0.0374   1.0000   0.0786
  -3.750  -0.2925   0.02442   0.01331  -0.0358   1.0000   0.0870
  -3.500  -0.2723   0.02348   0.01232  -0.0347   1.0000   0.1021
  -3.250  -0.2513   0.02249   0.01127  -0.0338   1.0000   0.1168
  -3.000  -0.2296   0.02154   0.01037  -0.0332   1.0000   0.1449
  -2.750  -0.2062   0.02024   0.00946  -0.0334   1.0000   0.2089
  -2.500  -0.1906   0.01841   0.00941  -0.0315   1.0000   0.5485
  -2.250  -0.1788   0.01832   0.00957  -0.0275   1.0000   0.6884
  -2.000  -0.1680   0.01826   0.00958  -0.0233   0.9999   0.7698
  -1.750  -0.1473   0.01812   0.00960  -0.0200   0.9922   0.8728
  -1.500  -0.0851   0.01800   0.00921  -0.0262   0.9878   1.0000
  -1.250  -0.0484   0.01817   0.00902  -0.0293   0.9795   1.0000
  -1.000  -0.0117   0.01837   0.00891  -0.0322   0.9712   1.0000
  -0.750   0.0260   0.01861   0.00888  -0.0352   0.9634   1.0000
  -0.500   0.0625   0.01886   0.00887  -0.0377   0.9550   1.0000
  -0.250   0.0974   0.01910   0.00892  -0.0399   0.9459   1.0000
   0.000   0.1367   0.01938   0.00903  -0.0428   0.9380   1.0000
   0.250   0.1707   0.01962   0.00913  -0.0447   0.9280   1.0000
   0.500   0.2052   0.01986   0.00927  -0.0465   0.9180   1.0000
   0.750   0.2436   0.02009   0.00944  -0.0489   0.9091   1.0000
   1.000   0.2796   0.02031   0.00961  -0.0508   0.8990   1.0000
   1.250   0.3129   0.02053   0.00981  -0.0522   0.8881   1.0000
   1.750   0.3841   0.02088   0.01020  -0.0553   0.8672   1.0000
   2.000   0.4197   0.02098   0.01034  -0.0566   0.8557   1.0000
   2.250   0.4532   0.02103   0.01045  -0.0574   0.8417   1.0000
   2.500   0.4874   0.02099   0.01052  -0.0579   0.8268   1.0000
   2.750   0.5161   0.02102   0.01063  -0.0576   0.8095   1.0000
   3.000   0.5456   0.02103   0.01074  -0.0574   0.7926   1.0000
   3.250   0.5753   0.02102   0.01089  -0.0571   0.7757   1.0000
   3.500   0.6057   0.02094   0.01094  -0.0567   0.7580   1.0000
   3.750   0.6324   0.02093   0.01106  -0.0557   0.7370   1.0000
   4.000   0.6608   0.02081   0.01108  -0.0548   0.7151   1.0000
   4.250   0.6860   0.02079   0.01126  -0.0535   0.6890   1.0000
   4.500   0.7116   0.02076   0.01137  -0.0521   0.6605   1.0000
   4.750   0.7369   0.02075   0.01147  -0.0507   0.6279   1.0000
   5.000   0.7612   0.02081   0.01162  -0.0491   0.5892   1.0000
   5.250   0.7849   0.02094   0.01175  -0.0474   0.5441   1.0000
   5.500   0.8067   0.02128   0.01203  -0.0455   0.4905   1.0000
   5.750   0.8259   0.02191   0.01241  -0.0435   0.4306   1.0000
   6.000   0.8428   0.02279   0.01305  -0.0416   0.3702   1.0000
   6.250   0.8593   0.02383   0.01387  -0.0399   0.3165   1.0000
   6.500   0.8753   0.02500   0.01487  -0.0383   0.2674   1.0000
   6.750   0.8906   0.02632   0.01600  -0.0368   0.2211   1.0000
   7.000   0.9064   0.02774   0.01731  -0.0354   0.1809   1.0000
   7.250   0.9220   0.02930   0.01881  -0.0341   0.1466   1.0000
   7.500   0.9389   0.03098   0.02042  -0.0328   0.1246   1.0000
   7.750   0.9576   0.03267   0.02218  -0.0317   0.1064   1.0000
   8.000   0.9760   0.03445   0.02404  -0.0305   0.0914   1.0000
   8.250   0.9960   0.03651   0.02621  -0.0295   0.0801   1.0000
   8.500   1.0126   0.03855   0.02837  -0.0283   0.0684   1.0000
   8.750   1.0286   0.04084   0.03072  -0.0272   0.0593   1.0000
   9.000   1.0439   0.04326   0.03348  -0.0260   0.0514   1.0000
   9.250   1.0594   0.04641   0.03687  -0.0249   0.0469   1.0000
   9.500   1.0688   0.04950   0.04056  -0.0232   0.0421   1.0000
   9.750   1.0751   0.05225   0.04358  -0.0217   0.0388   1.0000
  10.000   1.0795   0.05552   0.04704  -0.0203   0.0370   1.0000
  10.250   1.0792   0.05965   0.05138  -0.0188   0.0359   1.0000
  10.500   1.0701   0.06333   0.05545  -0.0167   0.0355   1.0000
  10.750   1.0571   0.06725   0.05971  -0.0151   0.0353   1.0000
  11.000   1.0418   0.07152   0.06426  -0.0145   0.0352   1.0000
  11.250   1.0240   0.07632   0.06931  -0.0150   0.0351   1.0000
  11.500   1.0057   0.08167   0.07486  -0.0167   0.0352   1.0000
  11.750   0.9870   0.08766   0.08102  -0.0195   0.0354   1.0000
  12.000   0.9678   0.09447   0.08796  -0.0234   0.0356   1.0000
  12.250   0.9495   0.10205   0.09563  -0.0282   0.0358   1.0000
  12.500   0.9132   0.11651   0.11022  -0.0392   0.0378   1.0000
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