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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.89 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq308-il-1000000-n5.txt
Download as CSV file: xf-hq308-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3025   0.11543   0.11385  -0.0274   1.0000   0.0038
  -7.250  -0.3175   0.06627   0.06473  -0.0567   0.9741   0.0023
  -7.000  -0.2911   0.05907   0.05749  -0.0701   0.9629   0.0023
  -6.500  -0.2535   0.04613   0.04427  -0.0858   0.9311   0.0021
  -6.250  -0.2382   0.04075   0.03867  -0.0889   0.9173   0.0021
  -6.000  -0.2209   0.03547   0.03314  -0.0910   0.9061   0.0020
  -5.750  -0.2018   0.02944   0.02675  -0.0923   0.8960   0.0020
  -5.500  -0.1861   0.01467   0.01064  -0.0921   0.8860   0.0020
  -5.250  -0.1604   0.01281   0.00841  -0.0918   0.8795   0.0023
  -5.000  -0.1336   0.01205   0.00745  -0.0917   0.8730   0.0024
  -4.500  -0.0807   0.01030   0.00538  -0.0914   0.8603   0.0030
  -4.250  -0.0536   0.00991   0.00490  -0.0914   0.8539   0.0032
  -4.000  -0.0264   0.00943   0.00434  -0.0913   0.8477   0.0035
  -3.750   0.0008   0.00902   0.00383  -0.0912   0.8413   0.0040
  -3.500   0.0284   0.00879   0.00355  -0.0911   0.8351   0.0047
  -3.250   0.0558   0.00848   0.00315  -0.0910   0.8281   0.0051
  -3.000   0.0834   0.00814   0.00273  -0.0910   0.8213   0.0053
  -2.750   0.1107   0.00748   0.00188  -0.0908   0.8128   0.0071
  -2.500   0.1383   0.00728   0.00161  -0.0907   0.8020   0.0078
  -2.250   0.1658   0.00715   0.00140  -0.0906   0.7906   0.0088
  -2.000   0.1936   0.00703   0.00121  -0.0905   0.7810   0.0090
  -1.750   0.2214   0.00695   0.00104  -0.0904   0.7724   0.0093
  -1.500   0.2491   0.00689   0.00093  -0.0904   0.7618   0.0101
  -1.250   0.2765   0.00679   0.00082  -0.0903   0.7475   0.0304
  -1.000   0.3037   0.00674   0.00076  -0.0902   0.7318   0.0476
  -0.750   0.3312   0.00666   0.00071  -0.0901   0.7187   0.0787
  -0.500   0.3587   0.00651   0.00067  -0.0902   0.7067   0.1371
  -0.250   0.3847   0.00558   0.00064  -0.0906   0.6944   0.4807
   0.000   0.4109   0.00533   0.00071  -0.0904   0.6779   0.6168
   0.250   0.4371   0.00530   0.00077  -0.0900   0.6559   0.6795
   0.500   0.4636   0.00538   0.00081  -0.0898   0.6322   0.7039
   0.750   0.4906   0.00548   0.00084  -0.0896   0.6107   0.7139
   1.000   0.5176   0.00558   0.00088  -0.0894   0.5898   0.7236
   1.250   0.5443   0.00571   0.00094  -0.0892   0.5658   0.7334
   1.500   0.5707   0.00588   0.00101  -0.0890   0.5348   0.7440
   1.750   0.5967   0.00608   0.00110  -0.0887   0.5013   0.7553
   2.000   0.6224   0.00632   0.00121  -0.0884   0.4631   0.7671
   2.250   0.6480   0.00655   0.00134  -0.0880   0.4269   0.7801
   2.500   0.6737   0.00677   0.00148  -0.0877   0.3945   0.7943
   2.750   0.6992   0.00700   0.00162  -0.0874   0.3627   0.8104
   3.000   0.7236   0.00730   0.00180  -0.0868   0.3172   0.8307
   3.250   0.7466   0.00765   0.00200  -0.0860   0.2653   0.8606
   3.500   0.7734   0.00775   0.00216  -0.0859   0.2295   1.0000
   3.750   0.7974   0.00827   0.00243  -0.0855   0.1762   1.0000
   4.000   0.8211   0.00881   0.00271  -0.0850   0.1264   1.0000
   4.250   0.8449   0.00935   0.00302  -0.0845   0.0819   1.0000
   4.500   0.8686   0.00990   0.00336  -0.0839   0.0445   1.0000
   4.750   0.8930   0.01036   0.00370  -0.0835   0.0209   1.0000
   5.000   0.9184   0.01067   0.00397  -0.0831   0.0134   1.0000
   5.250   0.9431   0.01108   0.00438  -0.0827   0.0038   1.0000
   5.500   0.9685   0.01139   0.00471  -0.0823   0.0031   1.0000
   5.750   0.9936   0.01175   0.00511  -0.0819   0.0023   1.0000
   6.000   1.0183   0.01217   0.00563  -0.0814   0.0019   1.0000
   6.250   1.0428   0.01258   0.00610  -0.0809   0.0018   1.0000
   6.500   1.0668   0.01305   0.00663  -0.0803   0.0018   1.0000
   6.750   1.0902   0.01359   0.00724  -0.0796   0.0018   1.0000
   7.000   1.1133   0.01418   0.00793  -0.0788   0.0017   1.0000
   7.250   1.1361   0.01476   0.00859  -0.0781   0.0016   1.0000
   7.500   1.1587   0.01534   0.00923  -0.0773   0.0015   1.0000
   7.750   1.1808   0.01596   0.00991  -0.0765   0.0013   1.0000
   8.000   1.2023   0.01664   0.01067  -0.0756   0.0012   1.0000
   8.250   1.2225   0.01746   0.01159  -0.0745   0.0011   1.0000
   8.500   1.2421   0.01832   0.01255  -0.0733   0.0011   1.0000
   8.750   1.2609   0.01923   0.01357  -0.0721   0.0010   1.0000
   9.000   1.2790   0.02019   0.01463  -0.0707   0.0010   1.0000
   9.250   1.2973   0.02108   0.01561  -0.0695   0.0009   1.0000
   9.500   1.3136   0.02214   0.01682  -0.0679   0.0009   1.0000
   9.750   1.3292   0.02320   0.01798  -0.0664   0.0008   1.0000
  10.000   1.3419   0.02451   0.01942  -0.0644   0.0007   1.0000
  10.250   1.3497   0.02624   0.02132  -0.0619   0.0007   1.0000
  10.500   1.3427   0.02902   0.02437  -0.0571   0.0006   1.0000
  10.750   1.3479   0.03038   0.02587  -0.0543   0.0006   1.0000
  11.000   1.3501   0.03202   0.02767  -0.0513   0.0006   1.0000
  11.250   1.3556   0.03334   0.02913  -0.0490   0.0006   1.0000
  11.500   1.3566   0.03517   0.03112  -0.0466   0.0006   1.0000
  11.750   1.3589   0.03694   0.03303  -0.0445   0.0005   1.0000
  12.000   1.3556   0.03938   0.03564  -0.0425   0.0005   1.0000
  12.250   1.3528   0.04189   0.03832  -0.0409   0.0005   1.0000
  12.500   1.3439   0.04526   0.04188  -0.0396   0.0005   1.0000
  12.750   1.3325   0.04922   0.04603  -0.0390   0.0005   1.0000
  13.000   1.3222   0.05335   0.05034  -0.0391   0.0005   1.0000
  13.250   1.3103   0.05810   0.05526  -0.0400   0.0005   1.0000
  13.500   1.2943   0.06398   0.06132  -0.0420   0.0005   1.0000
  13.750   1.2770   0.07077   0.06828  -0.0451   0.0005   1.0000
  14.000   1.2571   0.07888   0.07657  -0.0496   0.0004   1.0000
  14.250   1.2395   0.08747   0.08531  -0.0547   0.0004   1.0000
  14.500   1.2209   0.09702   0.09501  -0.0606   0.0004   1.0000
  14.750   1.1980   0.10821   0.10633  -0.0673   0.0005   1.0000
  15.000   1.1753   0.11968   0.11792  -0.0739   0.0005   1.0000
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