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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 100,000
Max Cl/Cd: 48.37 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1585-il-100000-n5.txt
Download as CSV file: xf-hq1585-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5363   0.08787   0.08299  -0.0206   1.0000   0.0260
  -9.000  -0.5468   0.07808   0.07333  -0.0286   1.0000   0.0243
  -8.500  -0.5620   0.06643   0.06162  -0.0380   1.0000   0.0237
  -8.250  -0.5692   0.06148   0.05658  -0.0406   1.0000   0.0235
  -8.000  -0.5738   0.05656   0.05148  -0.0425   1.0000   0.0234
  -7.750  -0.5749   0.05168   0.04633  -0.0436   1.0000   0.0234
  -7.500  -0.5717   0.04713   0.04143  -0.0442   1.0000   0.0235
  -7.250  -0.5646   0.04292   0.03679  -0.0441   1.0000   0.0237
  -7.000  -0.5549   0.03889   0.03226  -0.0437   1.0000   0.0240
  -6.750  -0.5439   0.03519   0.02827  -0.0432   1.0000   0.0253
  -6.500  -0.5276   0.03356   0.02651  -0.0426   1.0000   0.0276
  -6.250  -0.5108   0.03140   0.02403  -0.0416   1.0000   0.0296
  -6.000  -0.4932   0.02883   0.02102  -0.0404   1.0000   0.0308
  -5.750  -0.4744   0.02662   0.01840  -0.0390   1.0000   0.0321
  -5.500  -0.4548   0.02516   0.01656  -0.0376   1.0000   0.0345
  -5.250  -0.4364   0.02336   0.01458  -0.0364   1.0000   0.0374
  -5.000  -0.4174   0.02197   0.01309  -0.0350   1.0000   0.0392
  -4.750  -0.3982   0.02082   0.01183  -0.0336   1.0000   0.0411
  -4.500  -0.3790   0.01982   0.01067  -0.0322   1.0000   0.0435
  -4.250  -0.3483   0.01893   0.00961  -0.0330   0.9955   0.0479
  -4.000  -0.3159   0.01790   0.00858  -0.0345   0.9896   0.0543
  -3.750  -0.2821   0.01710   0.00763  -0.0360   0.9838   0.0609
  -3.500  -0.2490   0.01627   0.00676  -0.0374   0.9778   0.0729
  -3.250  -0.2167   0.01532   0.00606  -0.0389   0.9720   0.1167
  -3.000  -0.1861   0.01403   0.00564  -0.0406   0.9663   0.3006
  -2.750  -0.1576   0.01308   0.00558  -0.0412   0.9606   0.5029
  -2.500  -0.1290   0.01282   0.00572  -0.0409   0.9543   0.6303
  -2.250  -0.0999   0.01282   0.00583  -0.0404   0.9485   0.7111
  -2.000  -0.0714   0.01283   0.00580  -0.0401   0.9413   0.7530
  -1.750  -0.0381   0.01279   0.00568  -0.0409   0.9363   0.7771
  -1.500  -0.0102   0.01276   0.00558  -0.0407   0.9285   0.7987
  -1.250   0.0221   0.01270   0.00545  -0.0412   0.9233   0.8219
  -1.000   0.0488   0.01264   0.00540  -0.0406   0.9153   0.8449
  -0.750   0.0811   0.01258   0.00531  -0.0410   0.9098   0.8684
  -0.250   0.1504   0.01244   0.00515  -0.0429   0.8957   0.9213
   0.000   0.1906   0.01237   0.00506  -0.0453   0.8866   0.9439
   0.500   0.2735   0.01219   0.00482  -0.0507   0.8683   0.9872
   0.750   0.3039   0.01215   0.00473  -0.0512   0.8549   1.0000
   1.000   0.3285   0.01215   0.00469  -0.0505   0.8409   1.0000
   1.250   0.3537   0.01216   0.00465  -0.0497   0.8265   1.0000
   1.500   0.3791   0.01218   0.00463  -0.0490   0.8119   1.0000
   1.750   0.4046   0.01222   0.00467  -0.0483   0.7973   1.0000
   2.000   0.4302   0.01229   0.00474  -0.0477   0.7833   1.0000
   2.250   0.4559   0.01237   0.00482  -0.0470   0.7688   1.0000
   2.500   0.4813   0.01246   0.00495  -0.0464   0.7528   1.0000
   2.750   0.5067   0.01254   0.00510  -0.0458   0.7346   1.0000
   3.000   0.5323   0.01260   0.00521  -0.0450   0.7152   1.0000
   3.250   0.5576   0.01267   0.00532  -0.0442   0.6915   1.0000
   3.500   0.5826   0.01272   0.00537  -0.0432   0.6608   1.0000
   3.750   0.6071   0.01283   0.00546  -0.0421   0.6211   1.0000
   4.000   0.6307   0.01304   0.00551  -0.0408   0.5658   1.0000
   4.250   0.6520   0.01350   0.00560  -0.0392   0.4832   1.0000
   4.500   0.6716   0.01428   0.00587  -0.0376   0.3943   1.0000
   4.750   0.6922   0.01509   0.00631  -0.0366   0.3226   1.0000
   5.000   0.7143   0.01581   0.00680  -0.0359   0.2698   1.0000
   5.250   0.7372   0.01647   0.00739  -0.0352   0.2277   1.0000
   5.500   0.7599   0.01719   0.00799  -0.0346   0.1832   1.0000
   5.750   0.7814   0.01811   0.00868  -0.0339   0.1292   1.0000
   6.000   0.8019   0.01924   0.00959  -0.0330   0.0950   1.0000
   6.250   0.8235   0.02024   0.01057  -0.0322   0.0786   1.0000
   6.500   0.8448   0.02123   0.01156  -0.0313   0.0692   1.0000
   6.750   0.8662   0.02220   0.01272  -0.0304   0.0638   1.0000
   7.000   0.8860   0.02342   0.01399  -0.0294   0.0597   1.0000
   7.250   0.9072   0.02440   0.01511  -0.0286   0.0516   1.0000
   7.500   0.9276   0.02546   0.01629  -0.0279   0.0421   1.0000
   7.750   0.9451   0.02706   0.01794  -0.0268   0.0354   1.0000
   8.000   0.9643   0.02878   0.01993  -0.0256   0.0302   1.0000
   8.250   0.9818   0.03071   0.02195  -0.0244   0.0266   1.0000
   8.500   0.9986   0.03321   0.02465  -0.0233   0.0236   1.0000
   8.750   1.0169   0.03492   0.02670  -0.0221   0.0206   1.0000
   9.000   1.0327   0.03708   0.02919  -0.0210   0.0190   1.0000
   9.250   1.0462   0.03933   0.03167  -0.0197   0.0180   1.0000
   9.500   1.0568   0.04188   0.03443  -0.0185   0.0173   1.0000
   9.750   1.0625   0.04527   0.03810  -0.0169   0.0168   1.0000
  10.000   1.0635   0.04874   0.04203  -0.0149   0.0165   1.0000
  10.250   1.0584   0.05233   0.04602  -0.0128   0.0163   1.0000
  10.500   1.0470   0.05574   0.04974  -0.0104   0.0162   1.0000
  10.750   1.0321   0.05950   0.05379  -0.0090   0.0162   1.0000
  11.000   1.0163   0.06362   0.05815  -0.0088   0.0162   1.0000
  11.250   0.9980   0.06850   0.06325  -0.0100   0.0162   1.0000
  11.500   0.9787   0.07419   0.06914  -0.0126   0.0163   1.0000
  11.750   0.9595   0.08078   0.07589  -0.0167   0.0164   1.0000
  12.000   0.9413   0.08825   0.08349  -0.0219   0.0165   1.0000
  12.250   0.9228   0.09705   0.09238  -0.0282   0.0167   1.0000
  12.500   0.9062   0.10634   0.10172  -0.0344   0.0169   1.0000
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