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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 50,000
Max Cl/Cd: 37.34 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3512-il-50000-n5.txt
Download as CSV file: xf-hq3512-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3347   0.10497   0.09817  -0.0455   1.0000   0.0561
  -9.250  -0.3395   0.10190   0.09520  -0.0454   1.0000   0.0548
  -9.000  -0.3472   0.09882   0.09223  -0.0452   1.0000   0.0534
  -8.500  -0.3962   0.09071   0.08446  -0.0476   1.0000   0.0480
  -8.250  -0.4079   0.08846   0.08231  -0.0456   1.0000   0.0477
  -8.000  -0.4247   0.08610   0.08005  -0.0439   1.0000   0.0475
  -7.750  -0.4383   0.08345   0.07749  -0.0431   1.0000   0.0471
  -7.500  -0.4524   0.08033   0.07444  -0.0429   1.0000   0.0468
  -7.250  -0.4643   0.07719   0.07132  -0.0425   1.0000   0.0464
  -7.000  -0.4726   0.07346   0.06755  -0.0432   0.9993   0.0461
  -6.750  -0.4596   0.06742   0.06130  -0.0495   0.9917   0.0456
  -6.500  -0.4439   0.06143   0.05499  -0.0554   0.9846   0.0453
  -6.250  -0.4273   0.05608   0.04922  -0.0597   0.9775   0.0452
  -6.000  -0.4031   0.05094   0.04351  -0.0640   0.9719   0.0455
  -5.750  -0.3812   0.04669   0.03868  -0.0663   0.9653   0.0461
  -5.500  -0.3518   0.04273   0.03392  -0.0690   0.9603   0.0479
  -5.250  -0.3253   0.04037   0.03141  -0.0707   0.9553   0.0516
  -5.000  -0.2978   0.03818   0.02884  -0.0718   0.9496   0.0557
  -4.750  -0.2638   0.03577   0.02571  -0.0734   0.9453   0.0615
  -4.500  -0.2365   0.03418   0.02405  -0.0741   0.9402   0.0682
  -4.250  -0.2075   0.03266   0.02218  -0.0746   0.9348   0.0776
  -4.000  -0.1743   0.03149   0.02073  -0.0756   0.9306   0.0894
  -3.750  -0.1487   0.03044   0.01967  -0.0753   0.9250   0.0989
  -3.500  -0.1205   0.02960   0.01875  -0.0755   0.9195   0.1120
  -3.250  -0.0872   0.02874   0.01776  -0.0766   0.9155   0.1247
  -3.000  -0.0635   0.02811   0.01709  -0.0763   0.9087   0.1415
  -2.750  -0.0315   0.02732   0.01639  -0.0778   0.9036   0.1761
  -2.500   0.0012   0.02565   0.01584  -0.0801   0.8997   0.3434
  -2.250   0.0146   0.02542   0.01647  -0.0765   0.8920   0.5821
  -2.000   0.0403   0.02569   0.01670  -0.0750   0.8868   0.6734
  -1.750   0.0535   0.02595   0.01695  -0.0714   0.8787   0.7290
  -1.500   0.0674   0.02603   0.01712  -0.0667   0.8729   0.8002
  -1.250   0.0733   0.02594   0.01710  -0.0610   0.8648   0.8574
  -1.000   0.1036   0.02579   0.01686  -0.0604   0.8596   0.9036
  -0.750   0.1453   0.02585   0.01670  -0.0635   0.8539   0.9268
  -0.500   0.1906   0.02594   0.01660  -0.0676   0.8474   0.9564
  -0.250   0.2404   0.02595   0.01636  -0.0724   0.8429   1.0000
   0.000   0.2593   0.02621   0.01645  -0.0722   0.8330   1.0000
   0.250   0.2995   0.02628   0.01632  -0.0750   0.8280   1.0000
   0.750   0.3580   0.02674   0.01648  -0.0769   0.8122   1.0000
   1.000   0.3824   0.02708   0.01669  -0.0771   0.8027   1.0000
   1.250   0.4125   0.02733   0.01683  -0.0780   0.7948   1.0000
   1.500   0.4450   0.02750   0.01691  -0.0791   0.7871   1.0000
   1.750   0.4707   0.02782   0.01716  -0.0791   0.7775   1.0000
   2.000   0.5114   0.02766   0.01693  -0.0810   0.7706   1.0000
   2.250   0.5389   0.02768   0.01690  -0.0808   0.7581   1.0000
   2.500   0.5689   0.02754   0.01673  -0.0807   0.7453   1.0000
   2.750   0.5995   0.02736   0.01651  -0.0807   0.7327   1.0000
   3.000   0.6307   0.02719   0.01632  -0.0807   0.7211   1.0000
   3.250   0.6674   0.02686   0.01601  -0.0815   0.7123   1.0000
   3.500   0.6920   0.02697   0.01615  -0.0808   0.6995   1.0000
   3.750   0.7179   0.02702   0.01622  -0.0803   0.6866   1.0000
   4.000   0.7447   0.02702   0.01625  -0.0797   0.6736   1.0000
   4.250   0.7719   0.02697   0.01628  -0.0792   0.6601   1.0000
   4.500   0.7989   0.02693   0.01629  -0.0786   0.6460   1.0000
   4.750   0.8255   0.02687   0.01629  -0.0779   0.6306   1.0000
   5.000   0.8522   0.02679   0.01630  -0.0772   0.6142   1.0000
   5.250   0.8799   0.02667   0.01623  -0.0766   0.5972   1.0000
   5.500   0.9027   0.02676   0.01639  -0.0754   0.5769   1.0000
   5.750   0.9278   0.02678   0.01645  -0.0744   0.5559   1.0000
   6.000   0.9530   0.02684   0.01656  -0.0735   0.5338   1.0000
   6.250   0.9786   0.02693   0.01663  -0.0726   0.5104   1.0000
   6.500   1.0017   0.02723   0.01693  -0.0715   0.4863   1.0000
   6.750   1.0262   0.02755   0.01720  -0.0706   0.4633   1.0000
   7.000   1.0476   0.02810   0.01772  -0.0695   0.4410   1.0000
   7.250   1.0706   0.02867   0.01821  -0.0686   0.4210   1.0000
   7.500   1.0901   0.02944   0.01900  -0.0674   0.4016   1.0000
   7.750   1.1103   0.03023   0.01980  -0.0664   0.3841   1.0000
   8.000   1.1304   0.03106   0.02068  -0.0654   0.3679   1.0000
   8.250   1.1500   0.03193   0.02160  -0.0644   0.3527   1.0000
   8.500   1.1690   0.03284   0.02257  -0.0633   0.3383   1.0000
   8.750   1.1872   0.03378   0.02359  -0.0622   0.3245   1.0000
   9.000   1.2048   0.03475   0.02466  -0.0610   0.3113   1.0000
   9.250   1.2215   0.03577   0.02580  -0.0597   0.2983   1.0000
   9.500   1.2378   0.03683   0.02695  -0.0584   0.2856   1.0000
   9.750   1.2533   0.03793   0.02813  -0.0570   0.2730   1.0000
  10.000   1.2690   0.03906   0.02933  -0.0557   0.2607   1.0000
  10.250   1.2790   0.04035   0.03079  -0.0538   0.2486   1.0000
  10.500   1.2870   0.04179   0.03243  -0.0519   0.2369   1.0000
  10.750   1.2949   0.04325   0.03406  -0.0500   0.2256   1.0000
  11.000   1.3026   0.04470   0.03569  -0.0482   0.2148   1.0000
  11.250   1.3095   0.04619   0.03730  -0.0464   0.2042   1.0000
  11.500   1.3086   0.04819   0.03957  -0.0443   0.1938   1.0000
  11.750   1.3091   0.05015   0.04171  -0.0425   0.1838   1.0000
  12.000   1.3109   0.05201   0.04365  -0.0408   0.1743   1.0000
  12.250   1.3071   0.05444   0.04630  -0.0393   0.1647   1.0000
  12.500   1.3023   0.05714   0.04918  -0.0380   0.1555   1.0000
  12.750   1.2999   0.05959   0.05169  -0.0370   0.1469   1.0000
  13.000   1.2922   0.06284   0.05514  -0.0363   0.1383   1.0000
  13.250   1.2841   0.06635   0.05879  -0.0359   0.1302   1.0000
  13.500   1.2787   0.06944   0.06187  -0.0357   0.1224   1.0000
  13.750   1.2653   0.07420   0.06691  -0.0362   0.1151   1.0000
  14.000   1.2573   0.07802   0.07071  -0.0367   0.1078   1.0000
  14.250   1.2432   0.08346   0.07642  -0.0381   0.1015   1.0000
  14.500   1.2345   0.08786   0.08080  -0.0393   0.0949   1.0000
  14.750   1.2180   0.09432   0.08755  -0.0416   0.0898   1.0000
  15.000   1.2114   0.09868   0.09186  -0.0432   0.0832   1.0000
  15.250   1.1925   0.10636   0.09986  -0.0466   0.0797   1.0000
  15.500   1.1784   0.11308   0.10673  -0.0499   0.0753   1.0000
  15.750   1.1696   0.11865   0.11228  -0.0527   0.0700   1.0000
  16.000   1.1491   0.12780   0.12164  -0.0575   0.0684   1.0000
  16.250   1.1246   0.13857   0.13260  -0.0635   0.0684   1.0000
  16.500   1.0944   0.15193   0.14602  -0.0711   0.0694   1.0000
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