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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 500,000
Max Cl/Cd: 114.78 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq309-il-500000.txt
Download as CSV file: xf-hq309-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3758   0.08395   0.08182  -0.0366   1.0000   0.0133
  -8.000  -0.3817   0.08167   0.07960  -0.0356   1.0000   0.0136
  -7.750  -0.3976   0.08020   0.07820  -0.0325   1.0000   0.0137
  -7.500  -0.3967   0.07708   0.07510  -0.0347   0.9975   0.0142
  -7.250  -0.3744   0.07107   0.06910  -0.0447   0.9920   0.0150
  -7.000  -0.3475   0.06343   0.06142  -0.0589   0.9861   0.0159
  -6.750  -0.3078   0.05526   0.05305  -0.0734   0.9825   0.0182
  -6.500  -0.2777   0.05054   0.04810  -0.0797   0.9763   0.0188
  -6.250  -0.2580   0.03997   0.03715  -0.0888   0.9717   0.0197
  -6.000  -0.2291   0.03640   0.03346  -0.0929   0.9696   0.0207
  -5.750  -0.2046   0.03370   0.03061  -0.0947   0.9637   0.0216
  -5.500  -0.1758   0.03073   0.02742  -0.0969   0.9591   0.0231
  -5.250  -0.1446   0.02769   0.02407  -0.0988   0.9555   0.0254
  -5.000  -0.1147   0.02792   0.02402  -0.0979   0.9486   0.0284
  -4.750  -0.0936   0.01578   0.01067  -0.0975   0.9422   0.0135
  -4.500  -0.0682   0.01379   0.00834  -0.0966   0.9354   0.0128
  -4.250  -0.0415   0.01230   0.00665  -0.0962   0.9300   0.0132
  -4.000  -0.0156   0.01143   0.00567  -0.0957   0.9238   0.0143
  -3.750   0.0109   0.01079   0.00496  -0.0953   0.9175   0.0156
  -3.500   0.0380   0.01042   0.00452  -0.0950   0.9117   0.0177
  -3.250   0.0645   0.00998   0.00401  -0.0946   0.9049   0.0189
  -3.000   0.0913   0.00920   0.00312  -0.0943   0.8991   0.0249
  -2.750   0.1181   0.00879   0.00273  -0.0939   0.8918   0.0511
  -2.500   0.1455   0.00859   0.00252  -0.0938   0.8859   0.0686
  -2.250   0.1719   0.00822   0.00231  -0.0936   0.8778   0.1157
  -2.000   0.1956   0.00689   0.00209  -0.0937   0.8703   0.4658
  -1.750   0.2213   0.00658   0.00206  -0.0932   0.8623   0.5812
  -1.500   0.2481   0.00650   0.00204  -0.0928   0.8550   0.6277
  -1.250   0.2752   0.00645   0.00200  -0.0924   0.8478   0.6582
  -1.000   0.3023   0.00643   0.00198  -0.0921   0.8406   0.6828
  -0.750   0.3290   0.00640   0.00195  -0.0917   0.8332   0.7117
  -0.500   0.3548   0.00637   0.00198  -0.0910   0.8235   0.7467
  -0.250   0.3804   0.00634   0.00198  -0.0902   0.8133   0.7767
   0.000   0.4070   0.00632   0.00193  -0.0897   0.8041   0.7918
   0.250   0.4340   0.00629   0.00190  -0.0894   0.7945   0.8037
   0.500   0.4610   0.00627   0.00188  -0.0891   0.7854   0.8159
   0.750   0.4876   0.00625   0.00184  -0.0887   0.7754   0.8296
   1.000   0.5138   0.00622   0.00181  -0.0882   0.7637   0.8449
   1.250   0.5394   0.00617   0.00181  -0.0876   0.7515   0.8635
   1.500   0.5642   0.00609   0.00180  -0.0867   0.7398   0.8917
   1.750   0.5976   0.00597   0.00177  -0.0877   0.7274   0.9651
   2.000   0.6279   0.00604   0.00178  -0.0883   0.7141   1.0000
   2.250   0.6554   0.00613   0.00183  -0.0883   0.6998   1.0000
   2.500   0.6824   0.00624   0.00187  -0.0881   0.6839   1.0000
   2.750   0.7092   0.00637   0.00193  -0.0879   0.6667   1.0000
   3.000   0.7358   0.00650   0.00201  -0.0877   0.6468   1.0000
   3.250   0.7618   0.00667   0.00210  -0.0873   0.6246   1.0000
   3.500   0.7874   0.00686   0.00223  -0.0869   0.5980   1.0000
   3.750   0.8126   0.00710   0.00236  -0.0864   0.5657   1.0000
   4.000   0.8368   0.00740   0.00252  -0.0857   0.5289   1.0000
   4.250   0.8604   0.00778   0.00273  -0.0850   0.4862   1.0000
   4.500   0.8836   0.00821   0.00299  -0.0842   0.4409   1.0000
   4.750   0.9062   0.00871   0.00328  -0.0834   0.3941   1.0000
   5.000   0.9282   0.00927   0.00360  -0.0826   0.3409   1.0000
   5.250   0.9502   0.00986   0.00394  -0.0818   0.2920   1.0000
   5.500   0.9725   0.01042   0.00430  -0.0810   0.2507   1.0000
   5.750   0.9952   0.01094   0.00468  -0.0804   0.2152   1.0000
   6.000   1.0185   0.01140   0.00503  -0.0798   0.1879   1.0000
   6.250   1.0411   0.01193   0.00542  -0.0791   0.1589   1.0000
   6.500   1.0637   0.01245   0.00582  -0.0784   0.1321   1.0000
   6.750   1.0854   0.01306   0.00627  -0.0776   0.1006   1.0000
   7.000   1.1052   0.01385   0.00684  -0.0765   0.0652   1.0000
   7.250   1.1253   0.01461   0.00748  -0.0755   0.0412   1.0000
   7.500   1.1450   0.01541   0.00817  -0.0743   0.0233   1.0000
   7.750   1.1636   0.01634   0.00902  -0.0729   0.0095   1.0000
   8.000   1.1840   0.01706   0.00980  -0.0717   0.0074   1.0000
   8.250   1.2037   0.01782   0.01065  -0.0705   0.0066   1.0000
   8.500   1.2214   0.01876   0.01173  -0.0689   0.0061   1.0000
   8.750   1.2374   0.01981   0.01293  -0.0671   0.0059   1.0000
   9.000   1.2495   0.02117   0.01445  -0.0647   0.0057   1.0000
   9.250   1.2591   0.02265   0.01609  -0.0620   0.0056   1.0000
   9.500   1.2657   0.02419   0.01782  -0.0589   0.0056   1.0000
   9.750   1.2719   0.02572   0.01949  -0.0558   0.0056   1.0000
  10.000   1.2790   0.02723   0.02114  -0.0530   0.0056   1.0000
  10.250   1.2854   0.02897   0.02303  -0.0503   0.0057   1.0000
  10.500   1.2918   0.03079   0.02501  -0.0478   0.0057   1.0000
  10.750   1.2988   0.03253   0.02690  -0.0455   0.0058   1.0000
  11.000   1.3032   0.03465   0.02920  -0.0432   0.0058   1.0000
  11.250   1.3040   0.03733   0.03210  -0.0408   0.0057   1.0000
  11.500   1.3001   0.04063   0.03566  -0.0384   0.0057   1.0000
  11.750   1.2949   0.04388   0.03914  -0.0363   0.0056   1.0000
  12.000   1.2900   0.04657   0.04204  -0.0346   0.0055   1.0000
  12.250   1.2818   0.05008   0.04577  -0.0333   0.0055   1.0000
  12.500   1.2734   0.05364   0.04953  -0.0325   0.0055   1.0000
  12.750   1.2660   0.05715   0.05324  -0.0323   0.0054   1.0000
  13.000   1.2447   0.06322   0.05955  -0.0328   0.0055   1.0000
  13.250   1.2243   0.06962   0.06617  -0.0342   0.0056   1.0000
  13.500   1.2090   0.07537   0.07211  -0.0364   0.0056   1.0000
  13.750   1.1993   0.08061   0.07748  -0.0389   0.0057   1.0000
  14.000   1.1839   0.08738   0.08443  -0.0425   0.0057   1.0000
  14.250   1.1695   0.09455   0.09175  -0.0468   0.0057   1.0000
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