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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 200,000
Max Cl/Cd: 61.95 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1510-il-200000-n5.txt
Download as CSV file: xf-hq1510-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6037   0.06028   0.05684  -0.0437   1.0000   0.0101
  -9.500  -0.6278   0.05359   0.05001  -0.0487   1.0000   0.0100
  -9.250  -0.6486   0.04938   0.04566  -0.0491   1.0000   0.0099
  -9.000  -0.6636   0.04452   0.04052  -0.0489   1.0000   0.0099
  -8.750  -0.6729   0.03967   0.03525  -0.0478   1.0000   0.0100
  -8.500  -0.6730   0.03582   0.03090  -0.0462   1.0000   0.0105
  -8.250  -0.6694   0.03238   0.02705  -0.0444   1.0000   0.0106
  -8.000  -0.6637   0.02903   0.02329  -0.0424   1.0000   0.0109
  -7.750  -0.6525   0.02675   0.02072  -0.0406   1.0000   0.0112
  -7.500  -0.6391   0.02507   0.01883  -0.0389   1.0000   0.0117
  -7.250  -0.6249   0.02365   0.01716  -0.0370   1.0000   0.0122
  -7.000  -0.5972   0.02202   0.01528  -0.0377   0.9959   0.0129
  -6.750  -0.5662   0.02045   0.01347  -0.0390   0.9904   0.0139
  -6.500  -0.5332   0.01940   0.01220  -0.0404   0.9854   0.0157
  -6.250  -0.5028   0.01808   0.01079  -0.0416   0.9796   0.0178
  -6.000  -0.4702   0.01711   0.00972  -0.0430   0.9743   0.0199
  -5.750  -0.4382   0.01620   0.00864  -0.0441   0.9686   0.0226
  -5.500  -0.4075   0.01537   0.00777  -0.0451   0.9618   0.0280
  -5.250  -0.3745   0.01472   0.00706  -0.0465   0.9564   0.0363
  -5.000  -0.3443   0.01426   0.00653  -0.0471   0.9484   0.0447
  -4.750  -0.3119   0.01378   0.00604  -0.0484   0.9425   0.0561
  -4.500  -0.2828   0.01333   0.00559  -0.0489   0.9340   0.0684
  -4.250  -0.2522   0.01286   0.00508  -0.0496   0.9271   0.0813
  -4.000  -0.2229   0.01244   0.00465  -0.0500   0.9192   0.0987
  -3.750  -0.1945   0.01194   0.00428  -0.0504   0.9116   0.1345
  -3.500  -0.1671   0.01134   0.00395  -0.0506   0.9039   0.2058
  -3.250  -0.1413   0.01077   0.00364  -0.0506   0.8954   0.2873
  -3.000  -0.1164   0.01008   0.00343  -0.0503   0.8881   0.4166
  -2.750  -0.0922   0.00972   0.00338  -0.0496   0.8790   0.5122
  -2.500  -0.0660   0.00955   0.00334  -0.0490   0.8715   0.5720
  -2.250  -0.0397   0.00947   0.00329  -0.0485   0.8632   0.6116
  -2.000  -0.0134   0.00943   0.00327  -0.0479   0.8553   0.6470
  -1.750   0.0126   0.00940   0.00328  -0.0471   0.8475   0.6792
  -1.500   0.0389   0.00939   0.00326  -0.0466   0.8388   0.7002
  -1.250   0.0659   0.00938   0.00319  -0.0461   0.8312   0.7157
  -1.000   0.0922   0.00937   0.00318  -0.0456   0.8220   0.7328
  -0.750   0.1184   0.00936   0.00317  -0.0450   0.8137   0.7491
  -0.500   0.1450   0.00935   0.00313  -0.0445   0.8053   0.7628
  -0.250   0.1717   0.00933   0.00310  -0.0440   0.7952   0.7735
   0.000   0.1981   0.00931   0.00305  -0.0435   0.7840   0.7827
   0.250   0.2246   0.00929   0.00299  -0.0430   0.7714   0.7926
   0.750   0.2774   0.00926   0.00292  -0.0419   0.7476   0.8134
   1.000   0.3036   0.00924   0.00290  -0.0414   0.7346   0.8244
   1.250   0.3298   0.00923   0.00290  -0.0408   0.7213   0.8361
   1.500   0.3561   0.00922   0.00291  -0.0403   0.7090   0.8486
   1.750   0.3826   0.00922   0.00294  -0.0398   0.6967   0.8621
   2.000   0.4095   0.00922   0.00296  -0.0394   0.6834   0.8771
   2.250   0.4371   0.00923   0.00302  -0.0392   0.6693   0.8945
   2.500   0.4669   0.00925   0.00306  -0.0394   0.6533   0.9145
   2.750   0.5008   0.00930   0.00311  -0.0405   0.6349   0.9391
   3.000   0.5370   0.00937   0.00320  -0.0423   0.6119   0.9700
   3.250   0.5698   0.00949   0.00327  -0.0434   0.5848   1.0000
   3.500   0.5941   0.00969   0.00337  -0.0427   0.5532   1.0000
   3.750   0.6176   0.00997   0.00349  -0.0419   0.5119   1.0000
   4.000   0.6399   0.01037   0.00365  -0.0410   0.4594   1.0000
   4.250   0.6612   0.01089   0.00391  -0.0399   0.3998   1.0000
   4.500   0.6825   0.01148   0.00422  -0.0390   0.3412   1.0000
   4.750   0.7044   0.01205   0.00456  -0.0382   0.2947   1.0000
   5.000   0.7273   0.01255   0.00492  -0.0375   0.2630   1.0000
   5.250   0.7509   0.01300   0.00532  -0.0370   0.2397   1.0000
   5.500   0.7748   0.01342   0.00571  -0.0365   0.2173   1.0000
   5.750   0.7983   0.01388   0.00610  -0.0359   0.1894   1.0000
   6.000   0.8209   0.01445   0.00653  -0.0353   0.1535   1.0000
   6.250   0.8424   0.01513   0.00704  -0.0346   0.1191   1.0000
   6.500   0.8637   0.01586   0.00764  -0.0338   0.0925   1.0000
   6.750   0.8854   0.01654   0.00830  -0.0330   0.0752   1.0000
   7.000   0.9070   0.01722   0.00897  -0.0322   0.0643   1.0000
   7.250   0.9284   0.01791   0.00966  -0.0314   0.0556   1.0000
   7.500   0.9504   0.01850   0.01033  -0.0307   0.0492   1.0000
   7.750   0.9711   0.01923   0.01106  -0.0298   0.0434   1.0000
   8.000   0.9924   0.01985   0.01179  -0.0290   0.0395   1.0000
   8.250   1.0137   0.02045   0.01248  -0.0282   0.0342   1.0000
   8.500   1.0334   0.02122   0.01330  -0.0273   0.0304   1.0000
   8.750   1.0544   0.02182   0.01405  -0.0264   0.0263   1.0000
   9.000   1.0740   0.02256   0.01478  -0.0255   0.0203   1.0000
   9.250   1.0924   0.02340   0.01564  -0.0245   0.0150   1.0000
   9.500   1.1087   0.02442   0.01679  -0.0231   0.0119   1.0000
   9.750   1.1230   0.02561   0.01805  -0.0215   0.0099   1.0000
  10.000   1.1353   0.02691   0.01948  -0.0197   0.0089   1.0000
  10.250   1.1459   0.02818   0.02092  -0.0176   0.0083   1.0000
  10.500   1.1540   0.02951   0.02246  -0.0153   0.0078   1.0000
  10.750   1.1609   0.03092   0.02402  -0.0131   0.0075   1.0000
  11.000   1.1663   0.03248   0.02574  -0.0109   0.0071   1.0000
  11.250   1.1703   0.03418   0.02761  -0.0089   0.0069   1.0000
  11.500   1.1728   0.03607   0.02966  -0.0071   0.0067   1.0000
  11.750   1.1731   0.03822   0.03199  -0.0055   0.0065   1.0000
  12.000   1.1717   0.04066   0.03460  -0.0042   0.0064   1.0000
  12.250   1.1679   0.04346   0.03758  -0.0032   0.0063   1.0000
  12.500   1.1634   0.04650   0.04082  -0.0027   0.0062   1.0000
  12.750   1.1552   0.05019   0.04470  -0.0026   0.0061   1.0000
  13.000   1.1463   0.05419   0.04890  -0.0031   0.0061   1.0000
  13.250   1.1348   0.05888   0.05380  -0.0043   0.0060   1.0000
  13.500   1.1247   0.06364   0.05876  -0.0061   0.0061   1.0000
  13.750   1.1110   0.06938   0.06470  -0.0087   0.0060   1.0000
  14.000   1.0969   0.07564   0.07116  -0.0120   0.0060   1.0000
  14.250   1.0817   0.08266   0.07839  -0.0161   0.0060   1.0000
  14.500   1.0634   0.09084   0.08674  -0.0210   0.0060   1.0000
  14.750   1.0470   0.09916   0.09525  -0.0261   0.0061   1.0000
  15.000   1.0282   0.10858   0.10484  -0.0318   0.0062   1.0000
  15.250   1.0082   0.11868   0.11510  -0.0378   0.0063   1.0000
  15.500   0.9777   0.13215   0.12874  -0.0454   0.0065   1.0000
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