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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 200,000
Max Cl/Cd: 72.14 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2510-il-200000-n5.txt
Download as CSV file: xf-hq2510-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4136   0.08718   0.08371  -0.0379   1.0000   0.0114
  -9.000  -0.4166   0.08298   0.07956  -0.0395   1.0000   0.0113
  -8.750  -0.4206   0.07912   0.07577  -0.0409   1.0000   0.0109
  -8.500  -0.4274   0.07488   0.07160  -0.0426   1.0000   0.0108
  -8.250  -0.4407   0.07032   0.06713  -0.0442   1.0000   0.0108
  -8.000  -0.4597   0.06630   0.06321  -0.0457   1.0000   0.0105
  -7.750  -0.4737   0.06122   0.05812  -0.0489   0.9986   0.0103
  -7.500  -0.4606   0.05187   0.04849  -0.0593   0.9881   0.0105
  -7.250  -0.4455   0.04362   0.03983  -0.0658   0.9792   0.0107
  -7.000  -0.4258   0.03560   0.03120  -0.0706   0.9727   0.0108
  -6.750  -0.4058   0.02982   0.02473  -0.0725   0.9647   0.0109
  -6.500  -0.3785   0.02548   0.01971  -0.0742   0.9599   0.0111
  -6.250  -0.3520   0.02268   0.01639  -0.0747   0.9537   0.0115
  -6.000  -0.3227   0.02064   0.01395  -0.0754   0.9485   0.0120
  -5.750  -0.2928   0.01838   0.01141  -0.0764   0.9446   0.0132
  -5.500  -0.2656   0.01779   0.01074  -0.0766   0.9373   0.0152
  -5.250  -0.2347   0.01683   0.00958  -0.0773   0.9327   0.0176
  -5.000  -0.2071   0.01583   0.00840  -0.0773   0.9263   0.0191
  -4.750  -0.1789   0.01479   0.00731  -0.0777   0.9203   0.0226
  -4.500  -0.1495   0.01428   0.00668  -0.0780   0.9147   0.0288
  -4.250  -0.1219   0.01370   0.00609  -0.0781   0.9080   0.0394
  -4.000  -0.0923   0.01324   0.00558  -0.0785   0.9029   0.0500
  -3.750  -0.0657   0.01292   0.00522  -0.0784   0.8954   0.0629
  -3.500  -0.0367   0.01250   0.00477  -0.0787   0.8901   0.0755
  -3.250  -0.0104   0.01215   0.00441  -0.0784   0.8824   0.0922
  -3.000   0.0175   0.01172   0.00405  -0.0786   0.8766   0.1264
  -2.750   0.0429   0.01118   0.00378  -0.0784   0.8690   0.2098
  -2.500   0.0685   0.01043   0.00351  -0.0784   0.8630   0.3556
  -2.250   0.0922   0.00991   0.00351  -0.0778   0.8553   0.5090
  -2.000   0.1182   0.00973   0.00351  -0.0771   0.8491   0.5895
  -1.750   0.1441   0.00968   0.00350  -0.0765   0.8412   0.6308
  -1.500   0.1708   0.00964   0.00346  -0.0759   0.8347   0.6690
  -1.250   0.1956   0.00964   0.00352  -0.0750   0.8261   0.7077
  -1.000   0.2217   0.00961   0.00349  -0.0743   0.8187   0.7309
  -0.750   0.2481   0.00960   0.00345  -0.0737   0.8102   0.7473
  -0.500   0.2749   0.00957   0.00339  -0.0733   0.8022   0.7588
  -0.250   0.3022   0.00955   0.00332  -0.0730   0.7945   0.7686
   0.000   0.3291   0.00955   0.00328  -0.0728   0.7858   0.7789
   0.250   0.3559   0.00952   0.00323  -0.0723   0.7764   0.7890
   0.500   0.3823   0.00948   0.00315  -0.0718   0.7647   0.7995
   0.750   0.4085   0.00945   0.00309  -0.0712   0.7517   0.8107
   1.000   0.4348   0.00943   0.00306  -0.0707   0.7395   0.8229
   1.250   0.4610   0.00942   0.00307  -0.0703   0.7286   0.8363
   1.500   0.4871   0.00941   0.00307  -0.0697   0.7176   0.8511
   1.750   0.5133   0.00939   0.00307  -0.0692   0.7056   0.8684
   2.000   0.5403   0.00936   0.00307  -0.0688   0.6921   0.8910
   2.250   0.5717   0.00934   0.00310  -0.0693   0.6768   0.9231
   2.500   0.6090   0.00936   0.00310  -0.0713   0.6593   1.0000
   2.750   0.6356   0.00948   0.00316  -0.0711   0.6424   1.0000
   3.000   0.6619   0.00962   0.00324  -0.0708   0.6227   1.0000
   3.250   0.6876   0.00979   0.00336  -0.0704   0.5993   1.0000
   3.500   0.7128   0.00999   0.00346  -0.0699   0.5706   1.0000
   3.750   0.7374   0.01023   0.00359  -0.0693   0.5379   1.0000
   4.000   0.7611   0.01055   0.00376  -0.0685   0.5019   1.0000
   4.250   0.7843   0.01092   0.00398  -0.0677   0.4635   1.0000
   4.500   0.8070   0.01134   0.00428  -0.0669   0.4256   1.0000
   4.750   0.8294   0.01181   0.00459  -0.0660   0.3879   1.0000
   5.250   0.8734   0.01284   0.00532  -0.0644   0.3147   1.0000
   5.500   0.8955   0.01336   0.00573  -0.0636   0.2855   1.0000
   5.750   0.9181   0.01384   0.00619  -0.0629   0.2630   1.0000
   6.000   0.9404   0.01435   0.00665  -0.0621   0.2401   1.0000
   6.250   0.9614   0.01496   0.00711  -0.0612   0.2046   1.0000
   6.500   0.9825   0.01558   0.00760  -0.0604   0.1753   1.0000
   6.750   1.0037   0.01618   0.00812  -0.0595   0.1503   1.0000
   7.000   1.0238   0.01689   0.00870  -0.0586   0.1220   1.0000
   7.250   1.0433   0.01766   0.00937  -0.0576   0.0944   1.0000
   7.500   1.0609   0.01862   0.01013  -0.0563   0.0608   1.0000
   7.750   1.0727   0.02017   0.01131  -0.0543   0.0163   1.0000
   8.000   1.0902   0.02115   0.01231  -0.0529   0.0111   1.0000
   8.250   1.1070   0.02217   0.01345  -0.0513   0.0091   1.0000
   8.500   1.1241   0.02311   0.01456  -0.0498   0.0083   1.0000
   8.750   1.1407   0.02403   0.01561  -0.0483   0.0071   1.0000
   9.000   1.1558   0.02502   0.01674  -0.0467   0.0065   1.0000
   9.250   1.1673   0.02615   0.01801  -0.0446   0.0059   1.0000
   9.500   1.1746   0.02754   0.01956  -0.0419   0.0055   1.0000
   9.750   1.1796   0.02907   0.02131  -0.0392   0.0053   1.0000
  10.000   1.1845   0.03061   0.02300  -0.0367   0.0052   1.0000
  10.250   1.1891   0.03225   0.02480  -0.0343   0.0051   1.0000
  10.500   1.1934   0.03397   0.02668  -0.0322   0.0050   1.0000
  10.750   1.1969   0.03585   0.02871  -0.0302   0.0050   1.0000
  11.000   1.1992   0.03796   0.03098  -0.0284   0.0049   1.0000
  11.250   1.2010   0.04021   0.03340  -0.0268   0.0048   1.0000
  11.500   1.2021   0.04265   0.03601  -0.0255   0.0048   1.0000
  11.750   1.2020   0.04532   0.03887  -0.0243   0.0047   1.0000
  12.000   1.2014   0.04813   0.04186  -0.0234   0.0047   1.0000
  12.250   1.1990   0.05128   0.04520  -0.0228   0.0047   1.0000
  12.500   1.1950   0.05473   0.04886  -0.0225   0.0046   1.0000
  12.750   1.1896   0.05851   0.05284  -0.0225   0.0046   1.0000
  13.000   1.1825   0.06266   0.05721  -0.0231   0.0046   1.0000
  13.250   1.1748   0.06707   0.06182  -0.0241   0.0046   1.0000
  13.500   1.1640   0.07221   0.06718  -0.0258   0.0046   1.0000
  13.750   1.1523   0.07780   0.07297  -0.0280   0.0046   1.0000
  14.000   1.1397   0.08396   0.07933  -0.0309   0.0046   1.0000
  14.250   1.1270   0.09050   0.08607  -0.0344   0.0046   1.0000
  14.500   1.1121   0.09799   0.09376  -0.0387   0.0046   1.0000
  14.750   1.0982   0.10569   0.10163  -0.0432   0.0047   1.0000
  15.000   1.0842   0.11377   0.10987  -0.0481   0.0047   1.0000
  15.250   1.0693   0.12251   0.11876  -0.0535   0.0048   1.0000
  15.500   1.0541   0.13175   0.12814  -0.0591   0.0048   1.0000
  15.750   1.0397   0.14108   0.13760  -0.0648   0.0048   1.0000
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