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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 500,000
Max Cl/Cd: 105.63 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2510-il-500000.txt
Download as CSV file: xf-hq2510-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/10 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3324   0.08432   0.08225  -0.0397   1.0000   0.0174
  -9.500  -0.3334   0.08056   0.07851  -0.0400   1.0000   0.0179
  -9.250  -0.3338   0.07698   0.07494  -0.0405   1.0000   0.0182
  -9.000  -0.3349   0.07342   0.07141  -0.0410   1.0000   0.0185
  -8.750  -0.3386   0.06956   0.06759  -0.0416   1.0000   0.0188
  -8.500  -0.3434   0.06591   0.06397  -0.0420   1.0000   0.0192
  -8.250  -0.3545   0.06195   0.06006  -0.0423   1.0000   0.0193
  -8.000  -0.3746   0.05855   0.05673  -0.0412   0.9995   0.0191
  -7.750  -0.4576   0.05609   0.05396  -0.0585   0.9943   0.0174
  -7.500  -0.4430   0.04976   0.04744  -0.0655   0.9879   0.0179
  -7.250  -0.4187   0.04680   0.04438  -0.0698   0.9843   0.0188
  -7.000  -0.3934   0.04278   0.04019  -0.0743   0.9804   0.0200
  -6.750  -0.3678   0.03854   0.03568  -0.0778   0.9749   0.0222
  -6.500  -0.3451   0.02662   0.02269  -0.0820   0.9699   0.0183
  -6.250  -0.3232   0.01974   0.01504  -0.0819   0.9626   0.0133
  -6.000  -0.2948   0.01607   0.01081  -0.0822   0.9577   0.0125
  -5.750  -0.2663   0.01451   0.00903  -0.0824   0.9524   0.0127
  -5.500  -0.2395   0.01349   0.00788  -0.0822   0.9455   0.0136
  -5.250  -0.2116   0.01262   0.00690  -0.0822   0.9398   0.0148
  -5.000  -0.1863   0.01194   0.00609  -0.0816   0.9319   0.0161
  -4.750  -0.1606   0.01109   0.00511  -0.0811   0.9254   0.0178
  -4.500  -0.1348   0.01066   0.00467  -0.0807   0.9177   0.0225
  -4.250  -0.1088   0.01005   0.00401  -0.0803   0.9111   0.0312
  -4.000  -0.0824   0.00974   0.00368  -0.0799   0.9036   0.0445
  -3.750  -0.0556   0.00950   0.00339  -0.0797   0.8969   0.0540
  -3.500  -0.0289   0.00931   0.00315  -0.0794   0.8895   0.0630
  -3.250  -0.0022   0.00901   0.00289  -0.0792   0.8827   0.0803
  -3.000   0.0240   0.00860   0.00261  -0.0789   0.8753   0.1203
  -2.750   0.0488   0.00784   0.00235  -0.0788   0.8681   0.2648
  -2.500   0.0727   0.00703   0.00216  -0.0785   0.8605   0.4634
  -2.250   0.0986   0.00678   0.00212  -0.0781   0.8527   0.5501
  -2.000   0.1254   0.00669   0.00208  -0.0777   0.8453   0.5954
  -1.750   0.1522   0.00664   0.00206  -0.0774   0.8373   0.6300
  -1.500   0.1795   0.00662   0.00202  -0.0770   0.8306   0.6555
  -1.250   0.2067   0.00660   0.00202  -0.0768   0.8226   0.6770
  -1.000   0.2339   0.00660   0.00199  -0.0764   0.8153   0.6955
  -0.750   0.2604   0.00659   0.00200  -0.0759   0.8058   0.7200
  -0.500   0.2868   0.00658   0.00201  -0.0754   0.7961   0.7402
  -0.250   0.3138   0.00658   0.00197  -0.0750   0.7867   0.7537
   0.000   0.3407   0.00658   0.00196  -0.0747   0.7769   0.7666
   0.250   0.3680   0.00657   0.00195  -0.0744   0.7680   0.7774
   0.500   0.3954   0.00659   0.00193  -0.0742   0.7595   0.7875
   0.750   0.4224   0.00658   0.00192  -0.0740   0.7496   0.7968
   1.000   0.4495   0.00657   0.00192  -0.0737   0.7392   0.8069
   1.250   0.4764   0.00658   0.00193  -0.0734   0.7285   0.8178
   1.500   0.5032   0.00659   0.00193  -0.0731   0.7178   0.8299
   1.750   0.5296   0.00659   0.00194  -0.0727   0.7064   0.8428
   2.000   0.5556   0.00657   0.00196  -0.0722   0.6941   0.8577
   2.250   0.5810   0.00655   0.00200  -0.0715   0.6809   0.8763
   2.500   0.6055   0.00651   0.00202  -0.0706   0.6657   0.9046
   2.750   0.6404   0.00648   0.00204  -0.0720   0.6481   0.9625
   3.000   0.6731   0.00657   0.00209  -0.0732   0.6292   1.0000
   3.250   0.6995   0.00673   0.00217  -0.0730   0.6081   1.0000
   3.500   0.7256   0.00689   0.00226  -0.0727   0.5829   1.0000
   3.750   0.7510   0.00711   0.00238  -0.0722   0.5538   1.0000
   4.000   0.7754   0.00740   0.00252  -0.0716   0.5157   1.0000
   4.250   0.7988   0.00778   0.00273  -0.0709   0.4713   1.0000
   4.500   0.8218   0.00822   0.00296  -0.0702   0.4252   1.0000
   4.750   0.8449   0.00867   0.00323  -0.0695   0.3819   1.0000
   5.000   0.8683   0.00911   0.00351  -0.0688   0.3439   1.0000
   5.250   0.8918   0.00953   0.00380  -0.0682   0.3103   1.0000
   5.500   0.9148   0.01002   0.00415  -0.0675   0.2775   1.0000
   5.750   0.9365   0.01061   0.00450  -0.0667   0.2345   1.0000
   6.000   0.9597   0.01106   0.00483  -0.0661   0.2042   1.0000
   6.250   0.9830   0.01150   0.00517  -0.0655   0.1799   1.0000
   6.500   1.0061   0.01195   0.00553  -0.0649   0.1566   1.0000
   6.750   1.0284   0.01247   0.00595  -0.0642   0.1309   1.0000
   7.000   1.0490   0.01315   0.00644  -0.0632   0.0982   1.0000
   7.250   1.0662   0.01417   0.00712  -0.0618   0.0511   1.0000
   7.500   1.0802   0.01554   0.00820  -0.0597   0.0116   1.0000
   7.750   1.1004   0.01626   0.00897  -0.0585   0.0090   1.0000
   8.000   1.1200   0.01703   0.00987  -0.0572   0.0080   1.0000
   8.250   1.1398   0.01773   0.01067  -0.0560   0.0076   1.0000
   8.500   1.1582   0.01852   0.01157  -0.0546   0.0071   1.0000
   8.750   1.1751   0.01941   0.01259  -0.0529   0.0068   1.0000
   9.000   1.1897   0.02043   0.01371  -0.0510   0.0063   1.0000
   9.250   1.2028   0.02150   0.01489  -0.0489   0.0061   1.0000
   9.500   1.2125   0.02261   0.01611  -0.0462   0.0060   1.0000
   9.750   1.2195   0.02384   0.01744  -0.0432   0.0059   1.0000
  10.000   1.2254   0.02520   0.01893  -0.0402   0.0058   1.0000
  10.250   1.2314   0.02664   0.02049  -0.0375   0.0058   1.0000
  10.500   1.2364   0.02829   0.02227  -0.0348   0.0058   1.0000
  10.750   1.2416   0.03009   0.02423  -0.0324   0.0059   1.0000
  11.000   1.2462   0.03214   0.02645  -0.0300   0.0060   1.0000
  11.250   1.2497   0.03450   0.02901  -0.0278   0.0061   1.0000
  11.500   1.2517   0.03718   0.03194  -0.0256   0.0064   1.0000
  11.750   1.2494   0.04058   0.03561  -0.0234   0.0067   1.0000
  12.000   1.2441   0.04407   0.03940  -0.0215   0.0070   1.0000
  12.250   1.2351   0.04792   0.04350  -0.0200   0.0072   1.0000
  12.500   1.2234   0.05209   0.04790  -0.0190   0.0074   1.0000
  12.750   1.2073   0.05699   0.05304  -0.0186   0.0077   1.0000
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