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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 500,000
Max Cl/Cd: 96.22 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2195-il-500000.txt
Download as CSV file: xf-hq2195-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.1/9.5 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3814   0.08977   0.08754  -0.0329   1.0000   0.0255
 -10.000  -0.3842   0.08468   0.08247  -0.0352   1.0000   0.0257
  -9.750  -0.3889   0.07916   0.07697  -0.0376   1.0000   0.0258
  -9.500  -0.3949   0.07337   0.07119  -0.0402   1.0000   0.0258
  -9.250  -0.4036   0.06680   0.06464  -0.0435   1.0000   0.0259
  -9.000  -0.4230   0.05794   0.05576  -0.0500   1.0000   0.0259
  -8.750  -0.4454   0.05262   0.05040  -0.0536   1.0000   0.0259
  -8.500  -0.4697   0.04955   0.04730  -0.0534   1.0000   0.0258
  -8.250  -0.4886   0.04629   0.04397  -0.0519   1.0000   0.0259
  -8.000  -0.5154   0.03696   0.03449  -0.0542   0.9967   0.0265
  -7.750  -0.4950   0.03324   0.03072  -0.0573   0.9931   0.0271
  -7.500  -0.4734   0.03004   0.02743  -0.0602   0.9884   0.0278
  -7.250  -0.4493   0.02641   0.02363  -0.0635   0.9848   0.0292
  -7.000  -0.4180   0.02443   0.02109  -0.0660   0.9797   0.0333
  -6.750  -0.4491   0.02535   0.02096  -0.0662   0.9792   0.0242
  -6.500  -0.4194   0.02098   0.01604  -0.0679   0.9751   0.0234
  -6.250  -0.3856   0.01863   0.01335  -0.0696   0.9724   0.0239
  -6.000  -0.3503   0.01736   0.01183  -0.0713   0.9700   0.0250
  -5.750  -0.3209   0.01608   0.01037  -0.0718   0.9632   0.0254
  -5.500  -0.2880   0.01521   0.00934  -0.0728   0.9585   0.0258
  -5.250  -0.2591   0.01327   0.00728  -0.0734   0.9527   0.0267
  -5.000  -0.2313   0.01241   0.00639  -0.0735   0.9452   0.0280
  -4.750  -0.2022   0.01192   0.00587  -0.0738   0.9389   0.0296
  -4.500  -0.1758   0.01139   0.00529  -0.0735   0.9305   0.0309
  -4.250  -0.1486   0.01093   0.00475  -0.0733   0.9235   0.0323
  -4.000  -0.1221   0.01060   0.00436  -0.0729   0.9154   0.0334
  -3.750  -0.0963   0.00990   0.00361  -0.0726   0.9085   0.0368
  -3.500  -0.0695   0.00965   0.00334  -0.0724   0.9012   0.0410
  -3.250  -0.0424   0.00927   0.00293  -0.0722   0.8954   0.0485
  -3.000  -0.0157   0.00894   0.00262  -0.0719   0.8881   0.0668
  -2.750   0.0105   0.00845   0.00236  -0.0717   0.8808   0.1295
  -2.500   0.0341   0.00744   0.00207  -0.0715   0.8710   0.3342
  -2.250   0.0587   0.00683   0.00197  -0.0711   0.8620   0.5040
  -2.000   0.0848   0.00662   0.00193  -0.0706   0.8535   0.5719
  -1.750   0.1112   0.00652   0.00194  -0.0701   0.8454   0.6226
  -1.500   0.1382   0.00649   0.00193  -0.0697   0.8379   0.6573
  -1.250   0.1655   0.00648   0.00193  -0.0694   0.8308   0.6792
  -1.000   0.1928   0.00647   0.00193  -0.0691   0.8246   0.7013
  -0.750   0.2198   0.00646   0.00196  -0.0687   0.8187   0.7250
  -0.500   0.2466   0.00646   0.00199  -0.0682   0.8120   0.7490
  -0.250   0.2739   0.00646   0.00198  -0.0679   0.8063   0.7633
   0.000   0.3012   0.00643   0.00199  -0.0676   0.7992   0.7737
   0.250   0.3287   0.00643   0.00198  -0.0674   0.7928   0.7841
   0.750   0.3835   0.00642   0.00200  -0.0668   0.7782   0.8053
   1.000   0.4106   0.00641   0.00202  -0.0665   0.7701   0.8160
   1.250   0.4377   0.00643   0.00202  -0.0662   0.7620   0.8276
   1.500   0.4646   0.00641   0.00205  -0.0658   0.7522   0.8399
   1.750   0.4911   0.00641   0.00208  -0.0653   0.7421   0.8525
   2.000   0.5172   0.00640   0.00210  -0.0648   0.7304   0.8664
   2.250   0.5427   0.00639   0.00211  -0.0640   0.7154   0.8820
   2.500   0.5669   0.00636   0.00209  -0.0630   0.6915   0.9002
   2.750   0.5901   0.00635   0.00206  -0.0617   0.6580   0.9249
   3.000   0.6206   0.00645   0.00203  -0.0621   0.6011   0.9633
   3.250   0.6485   0.00693   0.00213  -0.0624   0.5187   1.0000
   3.500   0.6724   0.00740   0.00235  -0.0618   0.4664   1.0000
   3.750   0.6975   0.00778   0.00256  -0.0615   0.4282   1.0000
   4.000   0.7229   0.00812   0.00276  -0.0611   0.3974   1.0000
   4.250   0.7482   0.00847   0.00298  -0.0608   0.3664   1.0000
   4.500   0.7733   0.00882   0.00321  -0.0604   0.3351   1.0000
   4.750   0.7982   0.00919   0.00344  -0.0600   0.3027   1.0000
   5.000   0.8229   0.00958   0.00368  -0.0596   0.2649   1.0000
   5.250   0.8471   0.01003   0.00397  -0.0591   0.2246   1.0000
   5.500   0.8697   0.01066   0.00433  -0.0585   0.1735   1.0000
   5.750   0.8920   0.01133   0.00476  -0.0578   0.1283   1.0000
   6.000   0.9151   0.01192   0.00520  -0.0572   0.0998   1.0000
   6.250   0.9387   0.01245   0.00563  -0.0566   0.0816   1.0000
   6.500   0.9623   0.01296   0.00608  -0.0560   0.0678   1.0000
   6.750   0.9852   0.01356   0.00662  -0.0553   0.0542   1.0000
   7.000   1.0078   0.01419   0.00721  -0.0545   0.0431   1.0000
   7.250   1.0313   0.01468   0.00771  -0.0539   0.0373   1.0000
   7.500   1.0527   0.01542   0.00848  -0.0529   0.0333   1.0000
   7.750   1.0755   0.01596   0.00907  -0.0522   0.0311   1.0000
   8.000   1.0974   0.01658   0.00971  -0.0513   0.0290   1.0000
   8.250   1.1140   0.01776   0.01095  -0.0497   0.0267   1.0000
   8.500   1.1357   0.01834   0.01161  -0.0488   0.0257   1.0000
   8.750   1.1561   0.01905   0.01241  -0.0478   0.0246   1.0000
   9.000   1.1759   0.01979   0.01320  -0.0467   0.0234   1.0000
   9.250   1.1951   0.02054   0.01399  -0.0455   0.0222   1.0000
   9.500   1.2093   0.02186   0.01536  -0.0438   0.0210   1.0000
   9.750   1.2232   0.02337   0.01701  -0.0420   0.0202   1.0000
  10.000   1.2412   0.02420   0.01795  -0.0407   0.0196   1.0000
  10.250   1.2574   0.02523   0.01909  -0.0392   0.0189   1.0000
  10.500   1.2724   0.02624   0.02020  -0.0376   0.0181   1.0000
  10.750   1.2851   0.02720   0.02124  -0.0356   0.0174   1.0000
  11.000   1.2959   0.02815   0.02224  -0.0335   0.0167   1.0000
  11.250   1.3034   0.02981   0.02398  -0.0313   0.0161   1.0000
  11.500   1.3067   0.03272   0.02712  -0.0288   0.0155   1.0000
  11.750   1.3139   0.03378   0.02833  -0.0266   0.0151   1.0000
  12.000   1.3191   0.03534   0.03006  -0.0245   0.0148   1.0000
  12.250   1.3224   0.03715   0.03205  -0.0224   0.0144   1.0000
  12.500   1.3237   0.03919   0.03427  -0.0205   0.0141   1.0000
  12.750   1.3237   0.04138   0.03663  -0.0189   0.0138   1.0000
  13.000   1.3213   0.04393   0.03935  -0.0175   0.0136   1.0000
  13.250   1.3187   0.04652   0.04208  -0.0164   0.0133   1.0000
  13.500   1.3140   0.04942   0.04514  -0.0157   0.0131   1.0000
  13.750   1.3106   0.05223   0.04807  -0.0155   0.0128   1.0000
  14.000   1.3018   0.05605   0.05206  -0.0157   0.0127   1.0000
  14.250   1.2953   0.05969   0.05583  -0.0163   0.0125   1.0000
  14.500   1.2862   0.06399   0.06025  -0.0175   0.0123   1.0000
  14.750   1.2726   0.06932   0.06575  -0.0195   0.0122   1.0000
  15.000   1.2581   0.07518   0.07176  -0.0223   0.0121   1.0000
  15.250   1.2411   0.08207   0.07883  -0.0261   0.0120   1.0000
  15.500   1.2200   0.09047   0.08744  -0.0312   0.0121   1.0000
  15.750   1.1899   0.10165   0.09889  -0.0385   0.0123   1.0000
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