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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.22 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq309-il-1000000-n5.txt
Download as CSV file: xf-hq309-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3875   0.10802   0.10635  -0.0290   1.0000   0.0023
 -10.000  -0.3912   0.10218   0.10053  -0.0308   1.0000   0.0021
  -9.750  -0.3913   0.09778   0.09615  -0.0322   1.0000   0.0020
  -9.500  -0.3889   0.09461   0.09300  -0.0333   1.0000   0.0021
  -9.250  -0.3919   0.08990   0.08831  -0.0347   1.0000   0.0020
  -9.000  -0.3900   0.08714   0.08557  -0.0356   1.0000   0.0021
  -8.500  -0.3829   0.07901   0.07749  -0.0409   0.9913   0.0022
  -8.250  -0.3712   0.07418   0.07266  -0.0467   0.9842   0.0023
  -8.000  -0.3573   0.06758   0.06607  -0.0560   0.9753   0.0024
  -7.750  -0.3333   0.05784   0.05628  -0.0745   0.9620   0.0024
  -7.500  -0.3175   0.04980   0.04808  -0.0855   0.9427   0.0026
  -7.250  -0.3102   0.04317   0.04121  -0.0900   0.9227   0.0027
  -7.000  -0.3046   0.03567   0.03336  -0.0923   0.9070   0.0029
  -6.500  -0.2899   0.01555   0.01148  -0.0923   0.8844   0.0032
  -6.000  -0.2392   0.01350   0.00901  -0.0919   0.8717   0.0036
  -5.750  -0.2129   0.01283   0.00816  -0.0917   0.8655   0.0038
  -5.500  -0.1865   0.01210   0.00728  -0.0916   0.8595   0.0039
  -5.250  -0.1608   0.01100   0.00596  -0.0913   0.8532   0.0041
  -5.000  -0.1352   0.00992   0.00469  -0.0911   0.8474   0.0046
  -4.750  -0.1082   0.00952   0.00424  -0.0910   0.8413   0.0050
  -4.500  -0.0810   0.00918   0.00382  -0.0909   0.8356   0.0054
  -4.250  -0.0536   0.00883   0.00340  -0.0908   0.8294   0.0059
  -4.000  -0.0263   0.00852   0.00299  -0.0907   0.8231   0.0063
  -3.750   0.0013   0.00828   0.00269  -0.0907   0.8168   0.0067
  -3.500   0.0289   0.00808   0.00243  -0.0907   0.8100   0.0070
  -3.250   0.0566   0.00782   0.00210  -0.0906   0.8029   0.0073
  -3.000   0.0842   0.00758   0.00175  -0.0905   0.7940   0.0080
  -2.750   0.1118   0.00741   0.00150  -0.0904   0.7835   0.0098
  -2.500   0.1395   0.00729   0.00134  -0.0903   0.7732   0.0135
  -2.250   0.1670   0.00713   0.00122  -0.0903   0.7646   0.0297
  -2.000   0.1949   0.00705   0.00112  -0.0903   0.7563   0.0370
  -1.750   0.2227   0.00694   0.00103  -0.0903   0.7487   0.0544
  -1.500   0.2503   0.00682   0.00096  -0.0903   0.7392   0.0823
  -1.250   0.2774   0.00657   0.00088  -0.0903   0.7263   0.1561
  -1.000   0.3045   0.00634   0.00081  -0.0903   0.7112   0.2398
  -0.750   0.3313   0.00602   0.00074  -0.0904   0.6966   0.3538
  -0.500   0.3581   0.00574   0.00073  -0.0904   0.6841   0.4718
  -0.250   0.3853   0.00563   0.00074  -0.0903   0.6724   0.5316
   0.000   0.4123   0.00554   0.00079  -0.0902   0.6596   0.6000
   0.250   0.4389   0.00552   0.00084  -0.0900   0.6408   0.6538
   0.500   0.4656   0.00558   0.00089  -0.0897   0.6191   0.6811
   0.750   0.4927   0.00567   0.00092  -0.0896   0.6001   0.6902
   1.000   0.5198   0.00578   0.00096  -0.0894   0.5799   0.6986
   1.250   0.5465   0.00591   0.00102  -0.0892   0.5565   0.7072
   1.500   0.5731   0.00606   0.00109  -0.0890   0.5310   0.7155
   2.000   0.6252   0.00646   0.00128  -0.0884   0.4676   0.7344
   2.250   0.6510   0.00669   0.00141  -0.0881   0.4357   0.7441
   2.500   0.6769   0.00692   0.00154  -0.0878   0.4051   0.7543
   2.750   0.7028   0.00713   0.00167  -0.0876   0.3783   0.7655
   3.000   0.7286   0.00735   0.00181  -0.0873   0.3504   0.7770
   3.250   0.7540   0.00759   0.00198  -0.0869   0.3201   0.7894
   3.500   0.7794   0.00782   0.00215  -0.0865   0.2945   0.8029
   3.750   0.8046   0.00805   0.00233  -0.0861   0.2709   0.8189
   4.000   0.8298   0.00823   0.00250  -0.0857   0.2516   0.8387
   4.250   0.8533   0.00843   0.00269  -0.0850   0.2257   0.8705
   4.500   0.8790   0.00875   0.00296  -0.0848   0.1781   1.0000
   4.750   0.9027   0.00923   0.00324  -0.0843   0.1398   1.0000
   5.000   0.9260   0.00975   0.00356  -0.0837   0.1024   1.0000
   5.250   0.9494   0.01025   0.00389  -0.0831   0.0724   1.0000
   5.500   0.9712   0.01094   0.00435  -0.0823   0.0343   1.0000
   5.750   0.9942   0.01149   0.00479  -0.0816   0.0138   1.0000
   6.000   1.0177   0.01198   0.00521  -0.0809   0.0038   1.0000
   6.250   1.0427   0.01229   0.00554  -0.0805   0.0032   1.0000
   6.500   1.0673   0.01261   0.00591  -0.0801   0.0029   1.0000
   6.750   1.0915   0.01300   0.00634  -0.0795   0.0025   1.0000
   7.000   1.1151   0.01342   0.00682  -0.0789   0.0022   1.0000
   7.250   1.1379   0.01394   0.00743  -0.0781   0.0020   1.0000
   7.500   1.1600   0.01452   0.00809  -0.0773   0.0018   1.0000
   7.750   1.1803   0.01531   0.00898  -0.0761   0.0017   1.0000
   8.000   1.2020   0.01588   0.00960  -0.0752   0.0016   1.0000
   8.250   1.2242   0.01636   0.01012  -0.0745   0.0016   1.0000
   8.500   1.2454   0.01694   0.01076  -0.0735   0.0015   1.0000
   8.750   1.2660   0.01754   0.01142  -0.0725   0.0014   1.0000
   9.000   1.2854   0.01824   0.01220  -0.0714   0.0013   1.0000
   9.250   1.3040   0.01896   0.01300  -0.0701   0.0013   1.0000
   9.500   1.3210   0.01981   0.01396  -0.0686   0.0012   1.0000
   9.750   1.3369   0.02069   0.01494  -0.0669   0.0012   1.0000
  10.000   1.3520   0.02157   0.01591  -0.0651   0.0011   1.0000
  10.250   1.3641   0.02248   0.01692  -0.0629   0.0011   1.0000
  10.500   1.3742   0.02340   0.01793  -0.0603   0.0011   1.0000
  10.750   1.3832   0.02439   0.01902  -0.0577   0.0010   1.0000
  11.000   1.3920   0.02541   0.02013  -0.0553   0.0010   1.0000
  11.250   1.3979   0.02667   0.02151  -0.0527   0.0009   1.0000
  11.500   1.4027   0.02806   0.02303  -0.0501   0.0009   1.0000
  11.750   1.4087   0.02940   0.02447  -0.0479   0.0009   1.0000
  12.000   1.4109   0.03111   0.02631  -0.0455   0.0009   1.0000
  12.250   1.4163   0.03261   0.02791  -0.0438   0.0008   1.0000
  12.500   1.4164   0.03465   0.03011  -0.0418   0.0008   1.0000
  12.750   1.4190   0.03655   0.03212  -0.0403   0.0008   1.0000
  13.000   1.4183   0.03889   0.03458  -0.0389   0.0008   1.0000
  13.250   1.4161   0.04148   0.03730  -0.0378   0.0007   1.0000
  13.500   1.4113   0.04457   0.04054  -0.0370   0.0007   1.0000
  13.750   1.4039   0.04813   0.04425  -0.0366   0.0007   1.0000
  14.000   1.3950   0.05215   0.04842  -0.0367   0.0007   1.0000
  14.250   1.3844   0.05669   0.05311  -0.0375   0.0007   1.0000
  14.500   1.3707   0.06205   0.05863  -0.0390   0.0007   1.0000
  14.750   1.3537   0.06845   0.06522  -0.0414   0.0007   1.0000
  15.000   1.3408   0.07466   0.07158  -0.0442   0.0007   1.0000
  15.250   1.3179   0.08330   0.08041  -0.0486   0.0006   1.0000
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