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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 100,000
Max Cl/Cd: 60.93 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq308-il-100000-n5.txt
Download as CSV file: xf-hq308-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2895   0.10007   0.09542  -0.0321   1.0000   0.0380
  -9.250  -0.2887   0.09686   0.09224  -0.0327   1.0000   0.0392
  -8.750  -0.3731   0.10125   0.09633  -0.0311   1.0000   0.0339
  -8.500  -0.3692   0.09845   0.09357  -0.0312   1.0000   0.0365
  -8.250  -0.3683   0.09563   0.09082  -0.0320   1.0000   0.0391
  -8.000  -0.3680   0.09280   0.08805  -0.0324   1.0000   0.0391
  -7.750  -0.3692   0.09008   0.08536  -0.0326   1.0000   0.0388
  -7.250  -0.3864   0.08578   0.08135  -0.0333   1.0000   0.0421
  -7.000  -0.3893   0.08298   0.07856  -0.0331   1.0000   0.0417
  -6.750  -0.3954   0.07999   0.07570  -0.0390   1.0000   0.0430
  -6.500  -0.3966   0.07692   0.07261  -0.0412   1.0000   0.0432
  -6.250  -0.3961   0.07398   0.06956  -0.0437   1.0000   0.0436
  -6.000  -0.3923   0.07082   0.06631  -0.0445   1.0000   0.0436
  -5.750  -0.3757   0.06409   0.05957  -0.0478   0.9961   0.0446
  -5.500  -0.3499   0.05887   0.05421  -0.0526   0.9910   0.0450
  -5.250  -0.3237   0.05297   0.04821  -0.0551   0.9869   0.0268
  -5.000  -0.2922   0.04709   0.04202  -0.0607   0.9815   0.0236
  -4.750  -0.2513   0.04003   0.03426  -0.0662   0.9767   0.0201
  -4.250  -0.1845   0.03313   0.02643  -0.0711   0.9676   0.0189
  -4.000  -0.1498   0.02956   0.02233  -0.0735   0.9637   0.0188
  -3.750  -0.1131   0.02660   0.01881  -0.0756   0.9609   0.0189
  -3.500  -0.0829   0.02398   0.01574  -0.0763   0.9557   0.0197
  -3.250  -0.0502   0.02248   0.01405  -0.0779   0.9514   0.0240
  -3.000  -0.0142   0.02079   0.01200  -0.0792   0.9484   0.0260
  -2.750   0.0164   0.01935   0.01036  -0.0794   0.9435   0.0280
  -2.500   0.0484   0.01826   0.00911  -0.0800   0.9387   0.0305
  -2.250   0.0839   0.01721   0.00797  -0.0816   0.9352   0.0382
  -2.000   0.1142   0.01646   0.00730  -0.0823   0.9294   0.0759
  -1.750   0.1438   0.01441   0.00692  -0.0839   0.9250   0.4865
  -1.500   0.1717   0.01397   0.00694  -0.0829   0.9210   0.7042
  -1.250   0.1907   0.01377   0.00690  -0.0802   0.9130   0.7982
  -1.000   0.2198   0.01330   0.00661  -0.0789   0.9088   0.9132
  -0.750   0.2617   0.01320   0.00631  -0.0820   0.9031   1.0000
  -0.500   0.2956   0.01322   0.00609  -0.0834   0.8966   1.0000
  -0.250   0.3280   0.01325   0.00594  -0.0845   0.8895   1.0000
   0.000   0.3611   0.01325   0.00580  -0.0855   0.8822   1.0000
   0.250   0.3912   0.01328   0.00572  -0.0860   0.8733   1.0000
   0.500   0.4256   0.01323   0.00556  -0.0871   0.8667   1.0000
   0.750   0.4532   0.01329   0.00555  -0.0871   0.8566   1.0000
   1.000   0.4827   0.01332   0.00552  -0.0873   0.8474   1.0000
   1.250   0.5139   0.01327   0.00542  -0.0876   0.8380   1.0000
   1.500   0.5431   0.01323   0.00535  -0.0876   0.8263   1.0000
   1.750   0.5709   0.01323   0.00532  -0.0872   0.8135   1.0000
   2.000   0.5984   0.01325   0.00534  -0.0869   0.8008   1.0000
   2.250   0.6259   0.01327   0.00536  -0.0866   0.7876   1.0000
   2.500   0.6536   0.01328   0.00537  -0.0862   0.7733   1.0000
   2.750   0.6805   0.01328   0.00544  -0.0857   0.7559   1.0000
   3.000   0.7069   0.01331   0.00548  -0.0850   0.7359   1.0000
   3.250   0.7338   0.01334   0.00552  -0.0844   0.7157   1.0000
   3.500   0.7599   0.01343   0.00563  -0.0838   0.6938   1.0000
   3.750   0.7859   0.01354   0.00582  -0.0831   0.6694   1.0000
   4.000   0.8116   0.01368   0.00597  -0.0823   0.6413   1.0000
   4.250   0.8367   0.01387   0.00614  -0.0814   0.6077   1.0000
   4.500   0.8609   0.01414   0.00635  -0.0804   0.5675   1.0000
   4.750   0.8841   0.01451   0.00661  -0.0793   0.5208   1.0000
   5.000   0.9061   0.01501   0.00695  -0.0781   0.4703   1.0000
   5.250   0.9271   0.01564   0.00749  -0.0768   0.4204   1.0000
   5.500   0.9478   0.01634   0.00804  -0.0756   0.3733   1.0000
   5.750   0.9678   0.01711   0.00866  -0.0743   0.3265   1.0000
   6.000   0.9871   0.01795   0.00934  -0.0731   0.2810   1.0000
   6.250   1.0067   0.01880   0.01006  -0.0720   0.2388   1.0000
   6.500   1.0256   0.01973   0.01082  -0.0708   0.1923   1.0000
   6.750   1.0438   0.02078   0.01163  -0.0697   0.1453   1.0000
   7.000   1.0623   0.02187   0.01254  -0.0686   0.1007   1.0000
   7.250   1.0784   0.02331   0.01374  -0.0673   0.0569   1.0000
   7.750   1.1087   0.02664   0.01708  -0.0638   0.0213   1.0000
   8.000   1.1232   0.02829   0.01895  -0.0619   0.0168   1.0000
   8.250   1.1343   0.03026   0.02105  -0.0598   0.0136   1.0000
   8.500   1.1486   0.03175   0.02281  -0.0580   0.0115   1.0000
   8.750   1.1604   0.03354   0.02483  -0.0560   0.0103   1.0000
   9.000   1.1707   0.03556   0.02709  -0.0538   0.0097   1.0000
   9.250   1.1804   0.03773   0.02950  -0.0517   0.0094   1.0000
   9.500   1.1883   0.04001   0.03203  -0.0494   0.0090   1.0000
   9.750   1.1947   0.04253   0.03481  -0.0472   0.0088   1.0000
  10.000   1.1986   0.04525   0.03782  -0.0449   0.0086   1.0000
  10.250   1.1997   0.04817   0.04103  -0.0425   0.0085   1.0000
  10.500   1.1974   0.05134   0.04451  -0.0403   0.0084   1.0000
  10.750   1.1919   0.05472   0.04819  -0.0384   0.0083   1.0000
  11.000   1.1833   0.05842   0.05219  -0.0369   0.0083   1.0000
  11.250   1.1723   0.06249   0.05656  -0.0360   0.0083   1.0000
  11.500   1.1589   0.06704   0.06139  -0.0359   0.0083   1.0000
  11.750   1.1436   0.07216   0.06678  -0.0368   0.0083   1.0000
  12.000   1.1271   0.07790   0.07278  -0.0387   0.0084   1.0000
  12.250   1.1089   0.08456   0.07968  -0.0419   0.0084   1.0000
  12.500   1.0894   0.09231   0.08765  -0.0465   0.0085   1.0000
  12.750   1.0685   0.10145   0.09699  -0.0525   0.0087   1.0000
  13.000   1.0464   0.11235   0.10805  -0.0598   0.0089   1.0000
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