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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.18 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3011-il-1000000-n5.txt
Download as CSV file: xf-hq3011-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7075   0.04979   0.04805  -0.0705   1.0000   0.0032
 -11.750  -0.7618   0.03900   0.03700  -0.0777   0.9999   0.0032
 -11.500  -0.7551   0.03421   0.03197  -0.0837   0.9846   0.0034
 -11.250  -0.7424   0.02937   0.02675  -0.0887   0.9748   0.0034
 -11.000  -0.7224   0.02634   0.02342  -0.0916   0.9651   0.0035
 -10.750  -0.6997   0.02441   0.02126  -0.0931   0.9548   0.0037
 -10.500  -0.6799   0.02275   0.01936  -0.0936   0.9422   0.0038
 -10.000  -0.6428   0.02002   0.01619  -0.0927   0.9188   0.0040
  -9.750  -0.6223   0.01898   0.01497  -0.0922   0.9107   0.0041
  -9.500  -0.6008   0.01807   0.01388  -0.0917   0.9033   0.0043
  -9.250  -0.5786   0.01718   0.01284  -0.0913   0.8969   0.0044
  -9.000  -0.5553   0.01648   0.01200  -0.0909   0.8904   0.0045
  -8.750  -0.5316   0.01579   0.01118  -0.0906   0.8846   0.0045
  -8.500  -0.5071   0.01522   0.01048  -0.0903   0.8787   0.0046
  -8.000  -0.4611   0.01327   0.00821  -0.0895   0.8672   0.0051
  -7.750  -0.4358   0.01274   0.00760  -0.0892   0.8616   0.0053
  -7.500  -0.4101   0.01229   0.00706  -0.0890   0.8564   0.0055
  -7.250  -0.3839   0.01190   0.00661  -0.0889   0.8508   0.0058
  -7.000  -0.3577   0.01154   0.00618  -0.0887   0.8453   0.0061
  -6.750  -0.3312   0.01116   0.00573  -0.0886   0.8400   0.0065
  -6.500  -0.3047   0.01081   0.00530  -0.0885   0.8342   0.0067
  -6.250  -0.2781   0.01047   0.00488  -0.0883   0.8288   0.0069
  -6.000  -0.2511   0.01016   0.00451  -0.0882   0.8228   0.0070
  -5.750  -0.2244   0.00981   0.00408  -0.0881   0.8169   0.0072
  -5.500  -0.1974   0.00946   0.00367  -0.0880   0.8111   0.0076
  -5.250  -0.1703   0.00918   0.00332  -0.0879   0.8048   0.0080
  -5.000  -0.1429   0.00894   0.00303  -0.0878   0.7990   0.0086
  -4.750  -0.1154   0.00873   0.00278  -0.0878   0.7926   0.0093
  -4.500  -0.0879   0.00855   0.00254  -0.0877   0.7866   0.0101
  -4.250  -0.0602   0.00834   0.00231  -0.0877   0.7802   0.0127
  -4.000  -0.0330   0.00811   0.00212  -0.0876   0.7737   0.0228
  -3.750  -0.0051   0.00798   0.00198  -0.0876   0.7669   0.0283
  -3.250   0.0504   0.00776   0.00172  -0.0876   0.7507   0.0374
  -3.000   0.0781   0.00769   0.00160  -0.0875   0.7423   0.0415
  -2.750   0.1059   0.00758   0.00150  -0.0876   0.7343   0.0498
  -2.500   0.1338   0.00746   0.00140  -0.0876   0.7277   0.0626
  -2.250   0.1616   0.00732   0.00131  -0.0876   0.7206   0.0842
  -2.000   0.1893   0.00717   0.00122  -0.0877   0.7140   0.1117
  -1.750   0.2169   0.00701   0.00114  -0.0877   0.7053   0.1512
  -1.500   0.2443   0.00681   0.00106  -0.0877   0.6953   0.2072
  -1.250   0.2714   0.00661   0.00100  -0.0877   0.6839   0.2697
  -1.000   0.2976   0.00620   0.00092  -0.0877   0.6728   0.3988
  -0.750   0.3249   0.00603   0.00091  -0.0877   0.6626   0.4659
  -0.500   0.3526   0.00598   0.00091  -0.0877   0.6533   0.5015
  -0.250   0.3800   0.00593   0.00095  -0.0876   0.6440   0.5483
   0.000   0.4076   0.00590   0.00099  -0.0876   0.6341   0.5863
   0.250   0.4353   0.00592   0.00101  -0.0875   0.6229   0.6023
   0.500   0.4628   0.00598   0.00103  -0.0875   0.6086   0.6144
   1.000   0.5166   0.00618   0.00111  -0.0871   0.5670   0.6315
   1.250   0.5436   0.00629   0.00116  -0.0869   0.5476   0.6386
   1.500   0.5703   0.00643   0.00122  -0.0867   0.5256   0.6451
   2.000   0.6230   0.00675   0.00140  -0.0863   0.4773   0.6598
   2.250   0.6489   0.00696   0.00151  -0.0859   0.4497   0.6687
   2.500   0.6747   0.00716   0.00163  -0.0856   0.4231   0.6780
   2.750   0.7005   0.00736   0.00176  -0.0853   0.3983   0.6886
   3.250   0.7514   0.00778   0.00205  -0.0846   0.3468   0.7154
   3.500   0.7766   0.00798   0.00221  -0.0842   0.3219   0.7343
   3.750   0.8013   0.00818   0.00240  -0.0837   0.2993   0.7612
   4.000   0.8259   0.00833   0.00260  -0.0831   0.2819   0.8004
   4.250   0.8505   0.00851   0.00279  -0.0826   0.2660   0.8331
   4.500   0.8754   0.00871   0.00297  -0.0821   0.2503   0.8515
   4.750   0.9003   0.00891   0.00315  -0.0816   0.2359   0.8647
   5.000   0.9248   0.00914   0.00334  -0.0811   0.2194   0.8771
   5.250   0.9479   0.00943   0.00357  -0.0803   0.1960   0.8910
   5.500   0.9692   0.00975   0.00383  -0.0792   0.1696   0.9112
   5.750   0.9973   0.01014   0.00414  -0.0796   0.1386   1.0000
   6.000   1.0197   0.01061   0.00446  -0.0789   0.1127   1.0000
   6.250   1.0425   0.01103   0.00477  -0.0782   0.0946   1.0000
   6.500   1.0651   0.01147   0.00510  -0.0775   0.0763   1.0000
   6.750   1.0867   0.01197   0.00550  -0.0766   0.0581   1.0000
   7.000   1.1085   0.01244   0.00589  -0.0757   0.0434   1.0000
   7.250   1.1288   0.01302   0.00637  -0.0747   0.0278   1.0000
   7.500   1.1497   0.01354   0.00681  -0.0737   0.0176   1.0000
   7.750   1.1682   0.01423   0.00742  -0.0723   0.0051   1.0000
   8.000   1.1894   0.01467   0.00789  -0.0713   0.0036   1.0000
   8.250   1.2105   0.01511   0.00836  -0.0703   0.0032   1.0000
   8.500   1.2312   0.01554   0.00883  -0.0693   0.0029   1.0000
   8.750   1.2511   0.01601   0.00935  -0.0681   0.0026   1.0000
   9.000   1.2708   0.01645   0.00983  -0.0669   0.0025   1.0000
   9.250   1.2888   0.01691   0.01034  -0.0654   0.0024   1.0000
   9.500   1.3050   0.01741   0.01089  -0.0636   0.0023   1.0000
   9.750   1.3205   0.01794   0.01148  -0.0618   0.0022   1.0000
  10.000   1.3352   0.01852   0.01212  -0.0598   0.0021   1.0000
  10.250   1.3493   0.01914   0.01280  -0.0579   0.0020   1.0000
  10.500   1.3628   0.01982   0.01354  -0.0559   0.0019   1.0000
  10.750   1.3758   0.02054   0.01431  -0.0540   0.0018   1.0000
  11.000   1.3876   0.02136   0.01520  -0.0520   0.0017   1.0000
  11.250   1.3987   0.02224   0.01615  -0.0500   0.0016   1.0000
  11.500   1.4088   0.02321   0.01719  -0.0480   0.0015   1.0000
  11.750   1.4176   0.02430   0.01836  -0.0460   0.0015   1.0000
  12.000   1.4220   0.02575   0.01994  -0.0437   0.0014   1.0000
  12.250   1.4263   0.02726   0.02155  -0.0415   0.0014   1.0000
  12.500   1.4294   0.02891   0.02331  -0.0395   0.0014   1.0000
  12.750   1.4345   0.03046   0.02494  -0.0378   0.0014   1.0000
  13.000   1.4378   0.03223   0.02681  -0.0361   0.0014   1.0000
  13.250   1.4438   0.03384   0.02850  -0.0349   0.0013   1.0000
  13.500   1.4482   0.03564   0.03039  -0.0337   0.0013   1.0000
  13.750   1.4518   0.03760   0.03244  -0.0327   0.0013   1.0000
  14.000   1.4525   0.03992   0.03487  -0.0317   0.0013   1.0000
  14.250   1.4522   0.04245   0.03750  -0.0309   0.0013   1.0000
  14.500   1.4506   0.04524   0.04041  -0.0304   0.0013   1.0000
  14.750   1.4487   0.04819   0.04347  -0.0302   0.0013   1.0000
  15.000   1.4461   0.05140   0.04679  -0.0302   0.0013   1.0000
  15.250   1.4385   0.05542   0.05096  -0.0306   0.0012   1.0000
  15.500   1.4355   0.05905   0.05469  -0.0312   0.0012   1.0000
  15.750   1.4265   0.06372   0.05950  -0.0324   0.0012   1.0000
  16.000   1.4237   0.06771   0.06360  -0.0337   0.0012   1.0000
  16.250   1.4064   0.07421   0.07025  -0.0361   0.0012   1.0000
  16.500   1.4007   0.07911   0.07527  -0.0381   0.0012   1.0000
  16.750   1.3835   0.08628   0.08259  -0.0413   0.0012   1.0000
  17.000   1.3683   0.09337   0.08982  -0.0447   0.0012   1.0000
  17.250   1.3558   0.10017   0.09675  -0.0482   0.0012   1.0000
  17.500   1.3374   0.10836   0.10509  -0.0524   0.0012   1.0000
  17.750   1.3178   0.11697   0.11384  -0.0570   0.0012   1.0000
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