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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 100,000
Max Cl/Cd: 61.74 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3510-il-100000.txt
Download as CSV file: xf-hq3510-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3742   0.09989   0.09549  -0.0387   1.0000   0.0776
  -8.000  -0.3962   0.09911   0.09484  -0.0366   1.0000   0.0778
  -7.750  -0.4163   0.09784   0.09368  -0.0357   1.0000   0.0779
  -7.500  -0.4332   0.09555   0.09146  -0.0378   1.0000   0.0781
  -7.250  -0.4051   0.09045   0.08636  -0.0279   1.0000   0.0816
  -7.000  -0.4149   0.08872   0.08471  -0.0255   1.0000   0.0829
  -6.750  -0.4243   0.08665   0.08271  -0.0243   1.0000   0.0848
  -6.500  -0.4335   0.08426   0.08038  -0.0243   1.0000   0.0866
  -6.250  -0.4418   0.08114   0.07730  -0.0270   1.0000   0.0892
  -6.000  -0.4505   0.07730   0.07310  -0.0402   1.0000   0.0921
  -5.750  -0.4469   0.07267   0.06874  -0.0354   1.0000   0.0938
  -5.500  -0.4428   0.07033   0.06647  -0.0322   1.0000   0.0966
  -5.250  -0.4358   0.06706   0.06315  -0.0338   1.0000   0.1020
  -5.000  -0.4244   0.06223   0.05810  -0.0391   1.0000   0.1086
  -4.750  -0.4146   0.05967   0.05554  -0.0380   1.0000   0.1132
  -4.500  -0.3903   0.05534   0.05100  -0.0429   0.9981   0.1246
  -4.250  -0.3558   0.05143   0.04692  -0.0481   0.9935   0.1403
  -4.000  -0.3216   0.04779   0.04303  -0.0533   0.9883   0.1657
  -3.250  -0.1677   0.03207   0.02425  -0.0664   0.9777   0.0648
  -3.000  -0.1293   0.02936   0.02115  -0.0684   0.9735   0.0632
  -2.750  -0.0869   0.02753   0.01879  -0.0706   0.9699   0.0642
  -2.500  -0.0556   0.02555   0.01677  -0.0715   0.9645   0.0700
  -2.250  -0.0194   0.02441   0.01557  -0.0730   0.9594   0.0865
  -2.000   0.0209   0.02330   0.01458  -0.0755   0.9554   0.1231
  -1.750   0.0484   0.02250   0.01396  -0.0758   0.9481   0.1565
  -1.500   0.0800   0.02035   0.01394  -0.0766   0.9440   0.6468
  -1.250   0.0942   0.02046   0.01431  -0.0722   0.9360   0.7886
  -1.000   0.1172   0.02037   0.01429  -0.0698   0.9294   0.8692
  -0.750   0.1574   0.02019   0.01406  -0.0722   0.9215   1.0000
  -0.500   0.2028   0.02049   0.01406  -0.0763   0.9154   1.0000
  -0.250   0.2345   0.02078   0.01413  -0.0779   0.9064   1.0000
   0.000   0.2806   0.02104   0.01418  -0.0818   0.9008   1.0000
   0.250   0.3087   0.02134   0.01432  -0.0825   0.8910   1.0000
   0.500   0.3527   0.02155   0.01438  -0.0858   0.8850   1.0000
   0.750   0.3853   0.02174   0.01446  -0.0870   0.8751   1.0000
   1.000   0.4210   0.02181   0.01443  -0.0884   0.8645   1.0000
   1.250   0.4682   0.02152   0.01406  -0.0914   0.8547   1.0000
   1.500   0.5210   0.02095   0.01344  -0.0950   0.8459   1.0000
   1.750   0.5550   0.02082   0.01328  -0.0958   0.8347   1.0000
   2.000   0.5929   0.02061   0.01304  -0.0971   0.8262   1.0000
   2.250   0.6336   0.02022   0.01266  -0.0987   0.8185   1.0000
   2.500   0.6639   0.02012   0.01259  -0.0987   0.8075   1.0000
   2.750   0.6990   0.01979   0.01228  -0.0993   0.7979   1.0000
   3.000   0.7389   0.01922   0.01173  -0.1004   0.7897   1.0000
   3.250   0.7688   0.01897   0.01155  -0.1000   0.7773   1.0000
   3.500   0.7998   0.01863   0.01126  -0.0997   0.7645   1.0000
   3.750   0.8312   0.01824   0.01092  -0.0994   0.7511   1.0000
   4.000   0.8627   0.01782   0.01054  -0.0990   0.7365   1.0000
   4.250   0.8946   0.01735   0.01016  -0.0986   0.7203   1.0000
   4.500   0.9211   0.01712   0.00997  -0.0975   0.6996   1.0000
   4.750   0.9515   0.01672   0.00958  -0.0968   0.6776   1.0000
   5.000   0.9774   0.01654   0.00939  -0.0955   0.6493   1.0000
   5.250   1.0003   0.01651   0.00939  -0.0939   0.6133   1.0000
   5.500   1.0234   0.01660   0.00936  -0.0922   0.5716   1.0000
   5.750   1.0452   0.01693   0.00948  -0.0905   0.5267   1.0000
   6.000   1.0659   0.01752   0.00983  -0.0889   0.4846   1.0000
   6.250   1.0867   0.01826   0.01036  -0.0876   0.4494   1.0000
   6.500   1.1079   0.01904   0.01104  -0.0864   0.4201   1.0000
   6.750   1.1296   0.01985   0.01173  -0.0854   0.3953   1.0000
   7.000   1.1508   0.02064   0.01248  -0.0843   0.3723   1.0000
   7.250   1.1720   0.02145   0.01328  -0.0833   0.3513   1.0000
   7.500   1.1926   0.02227   0.01409  -0.0822   0.3311   1.0000
   7.750   1.2134   0.02315   0.01499  -0.0812   0.3120   1.0000
   8.000   1.2325   0.02403   0.01596  -0.0798   0.2920   1.0000
   8.250   1.2518   0.02500   0.01687  -0.0786   0.2721   1.0000
   8.500   1.2667   0.02588   0.01790  -0.0767   0.2508   1.0000
   8.750   1.2776   0.02660   0.01862  -0.0743   0.2281   1.0000
   9.000   1.2826   0.02709   0.01924  -0.0711   0.2042   1.0000
   9.250   1.2855   0.02760   0.01987  -0.0676   0.1782   1.0000
   9.500   1.2851   0.02834   0.02057  -0.0639   0.1483   1.0000
   9.750   1.2834   0.02996   0.02197  -0.0604   0.1089   1.0000
  10.000   1.2709   0.03316   0.02479  -0.0559   0.0667   1.0000
  10.250   1.2631   0.03611   0.02764  -0.0522   0.0513   1.0000
  10.500   1.2595   0.03889   0.03052  -0.0493   0.0450   1.0000
  10.750   1.2614   0.04134   0.03305  -0.0470   0.0405   1.0000
  11.000   1.2658   0.04449   0.03613  -0.0450   0.0372   1.0000
  11.250   1.2762   0.04678   0.03869  -0.0434   0.0346   1.0000
  11.500   1.2841   0.04924   0.04134  -0.0419   0.0320   1.0000
  11.750   1.2906   0.05185   0.04406  -0.0407   0.0300   1.0000
  12.000   1.3020   0.05517   0.04749  -0.0397   0.0286   1.0000
  12.250   1.3136   0.05976   0.05235  -0.0387   0.0279   1.0000
  12.500   1.3132   0.06429   0.05721  -0.0375   0.0277   1.0000
  12.750   1.3061   0.06866   0.06185  -0.0364   0.0276   1.0000
  13.000   1.2955   0.07298   0.06651  -0.0356   0.0277   1.0000
  13.250   1.2830   0.07736   0.07118  -0.0353   0.0277   1.0000
  13.500   1.2683   0.08206   0.07614  -0.0356   0.0278   1.0000
  13.750   1.2526   0.08696   0.08130  -0.0366   0.0279   1.0000
  14.000   1.2352   0.09235   0.08694  -0.0383   0.0281   1.0000
  14.250   1.2164   0.09824   0.09308  -0.0410   0.0283   1.0000
  14.500   1.1947   0.10512   0.10022  -0.0449   0.0286   1.0000
  14.750   1.1690   0.11368   0.10907  -0.0505   0.0291   1.0000
  15.000   1.1354   0.12549   0.12115  -0.0590   0.0299   1.0000
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