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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 50,000
Max Cl/Cd: 39.03 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-50000.txt
Download as CSV file: xf-hq2590sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4127   0.10684   0.09976  -0.0195   1.0000   0.2412
  -8.750  -0.4353   0.10673   0.09983  -0.0211   1.0000   0.2507
  -8.500  -0.4257   0.10311   0.09625  -0.0200   1.0000   0.2650
  -8.250  -0.4211   0.10011   0.09328  -0.0191   1.0000   0.2797
  -8.000  -0.4046   0.09588   0.08907  -0.0173   1.0000   0.2976
  -7.750  -0.3971   0.09322   0.08646  -0.0154   1.0000   0.3215
  -7.500  -0.3901   0.09023   0.08353  -0.0136   1.0000   0.3433
  -7.250  -0.3919   0.08844   0.08184  -0.0115   1.0000   0.3668
  -7.000  -0.3757   0.08492   0.07834  -0.0094   1.0000   0.3911
  -6.750  -0.3742   0.08268   0.07618  -0.0069   1.0000   0.4160
  -6.500  -0.3846   0.08179   0.07544  -0.0033   1.0000   0.4414
  -6.250  -0.3760   0.07920   0.07290  -0.0004   1.0000   0.4709
  -6.000  -0.3685   0.07674   0.07048   0.0027   1.0000   0.5006
  -5.750  -0.3337   0.07214   0.06583   0.0037   1.0000   0.5395
  -4.750  -0.3964   0.04442   0.03646  -0.0464   1.0000   0.1626
  -4.500  -0.3701   0.04044   0.03193  -0.0473   1.0000   0.1456
  -4.250  -0.3468   0.03729   0.02846  -0.0476   1.0000   0.1416
  -4.000  -0.3211   0.03464   0.02532  -0.0479   1.0000   0.1399
  -3.750  -0.2941   0.03223   0.02238  -0.0479   1.0000   0.1374
  -3.500  -0.2671   0.03019   0.01984  -0.0476   1.0000   0.1361
  -3.250  -0.2416   0.02851   0.01787  -0.0470   1.0000   0.1387
  -3.000  -0.2158   0.02726   0.01626  -0.0464   1.0000   0.1460
  -2.750  -0.1917   0.02578   0.01479  -0.0454   1.0000   0.1539
  -2.500  -0.1681   0.02468   0.01354  -0.0440   1.0000   0.1636
  -2.250  -0.1450   0.02356   0.01252  -0.0430   1.0000   0.1854
  -2.000  -0.1187   0.02221   0.01139  -0.0427   1.0000   0.2260
  -1.750  -0.1124   0.01943   0.01150  -0.0361   1.0000   0.7458
  -1.500  -0.1108   0.01862   0.01095  -0.0269   1.0000   1.0000
  -1.250  -0.0848   0.01873   0.01051  -0.0278   1.0000   1.0000
  -1.000  -0.0587   0.01890   0.01025  -0.0288   1.0000   1.0000
  -0.750  -0.0329   0.01912   0.01012  -0.0296   1.0000   1.0000
  -0.500  -0.0076   0.01939   0.01009  -0.0303   1.0000   1.0000
  -0.250   0.0170   0.01969   0.01013  -0.0308   1.0000   1.0000
   0.000   0.0412   0.02004   0.01026  -0.0312   1.0000   1.0000
   0.250   0.0648   0.02042   0.01045  -0.0315   1.0000   1.0000
   0.500   0.0879   0.02084   0.01071  -0.0318   1.0000   1.0000
   0.750   0.1106   0.02130   0.01102  -0.0320   1.0000   1.0000
   1.000   0.1328   0.02180   0.01141  -0.0322   1.0000   1.0000
   1.250   0.1545   0.02235   0.01187  -0.0323   1.0000   1.0000
   1.500   0.1757   0.02295   0.01240  -0.0325   1.0000   1.0000
   1.750   0.1962   0.02361   0.01302  -0.0326   1.0000   1.0000
   2.000   0.2159   0.02435   0.01373  -0.0328   1.0000   1.0000
   2.250   0.2348   0.02518   0.01456  -0.0331   1.0000   1.0000
   2.500   0.2941   0.02684   0.01627  -0.0408   0.9779   1.0000
   2.750   0.3552   0.02830   0.01781  -0.0484   0.9530   1.0000
   3.000   0.4166   0.02947   0.01912  -0.0553   0.9269   1.0000
   3.250   0.4707   0.03024   0.02005  -0.0605   0.8987   1.0000
   3.500   0.5243   0.03076   0.02076  -0.0650   0.8699   1.0000
   3.750   0.5777   0.03097   0.02122  -0.0688   0.8407   1.0000
   4.000   0.6313   0.03083   0.02133  -0.0720   0.8117   1.0000
   4.250   0.6850   0.03030   0.02111  -0.0744   0.7831   1.0000
   4.500   0.7334   0.02949   0.02057  -0.0754   0.7545   1.0000
   4.750   0.7792   0.02838   0.01971  -0.0752   0.7251   1.0000
   5.000   0.8243   0.02683   0.01842  -0.0742   0.6932   1.0000
   5.250   0.8564   0.02575   0.01747  -0.0717   0.6546   1.0000
   5.500   0.8880   0.02462   0.01639  -0.0690   0.6119   1.0000
   5.750   0.9168   0.02390   0.01559  -0.0662   0.5639   1.0000
   6.000   0.9403   0.02409   0.01556  -0.0635   0.5092   1.0000
   6.250   0.9611   0.02499   0.01611  -0.0608   0.4475   1.0000
   6.500   0.9765   0.02647   0.01720  -0.0578   0.3764   1.0000
   6.750   0.9906   0.02827   0.01855  -0.0549   0.3068   1.0000
   7.000   1.0061   0.02993   0.01982  -0.0525   0.2539   1.0000
   7.250   1.0228   0.03159   0.02127  -0.0506   0.2132   1.0000
   7.500   1.0432   0.03366   0.02316  -0.0493   0.1821   1.0000
   7.750   1.0658   0.03608   0.02560  -0.0482   0.1592   1.0000
   8.000   1.0902   0.03884   0.02833  -0.0475   0.1432   1.0000
   8.250   1.1108   0.04211   0.03211  -0.0462   0.1341   1.0000
   8.500   1.1296   0.04536   0.03558  -0.0451   0.1257   1.0000
   8.750   1.1429   0.04879   0.03953  -0.0434   0.1201   1.0000
   9.000   1.1590   0.05267   0.04368  -0.0422   0.1169   1.0000
   9.250   1.1704   0.05730   0.04857  -0.0409   0.1145   1.0000
   9.500   1.1674   0.06163   0.05351  -0.0384   0.1135   1.0000
   9.750   1.1596   0.06620   0.05859  -0.0361   0.1129   1.0000
  10.000   1.1477   0.07097   0.06375  -0.0341   0.1129   1.0000
  10.250   1.1329   0.07587   0.06894  -0.0324   0.1133   1.0000
  10.500   1.1174   0.08081   0.07408  -0.0310   0.1139   1.0000
  10.750   1.1043   0.08593   0.07932  -0.0301   0.1146   1.0000
  11.000   1.0148   0.09629   0.08994  -0.0348   0.1267   1.0000
  11.250   1.0057   0.10306   0.09673  -0.0370   0.1281   1.0000
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