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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 500,000
Max Cl/Cd: 84.68 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1585-il-500000.txt
Download as CSV file: xf-hq1585-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8.5 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5293   0.10321   0.10090  -0.0114   1.0000   0.0191
 -10.000  -0.5268   0.09878   0.09649  -0.0140   1.0000   0.0195
  -7.750  -0.5553   0.03263   0.02995  -0.0449   1.0000   0.0205
  -7.500  -0.5493   0.02905   0.02633  -0.0450   1.0000   0.0213
  -7.250  -0.5371   0.02707   0.02432  -0.0447   1.0000   0.0222
  -7.000  -0.5818   0.02497   0.02059  -0.0416   1.0000   0.0148
  -6.750  -0.5693   0.02229   0.01757  -0.0395   1.0000   0.0149
  -6.500  -0.5499   0.02073   0.01582  -0.0387   0.9989   0.0156
  -6.250  -0.5151   0.01903   0.01391  -0.0408   0.9953   0.0165
  -6.000  -0.4811   0.01731   0.01195  -0.0424   0.9910   0.0176
  -5.750  -0.4453   0.01660   0.01107  -0.0441   0.9867   0.0194
  -5.500  -0.4114   0.01431   0.00852  -0.0458   0.9834   0.0211
  -5.250  -0.3781   0.01319   0.00734  -0.0472   0.9782   0.0228
  -5.000  -0.3436   0.01257   0.00666  -0.0488   0.9728   0.0250
  -4.750  -0.3084   0.01200   0.00603  -0.0504   0.9679   0.0273
  -4.500  -0.2767   0.01150   0.00545  -0.0512   0.9597   0.0283
  -4.250  -0.2472   0.01034   0.00421  -0.0518   0.9519   0.0320
  -4.000  -0.2181   0.00998   0.00381  -0.0521   0.9431   0.0357
  -3.750  -0.1905   0.00969   0.00344  -0.0519   0.9341   0.0388
  -3.500  -0.1639   0.00918   0.00289  -0.0516   0.9260   0.0489
  -3.250  -0.1383   0.00866   0.00249  -0.0512   0.9168   0.0840
  -3.000  -0.1140   0.00783   0.00220  -0.0510   0.9090   0.2289
  -2.750  -0.0888   0.00731   0.00202  -0.0507   0.9012   0.3332
  -2.500  -0.0638   0.00678   0.00189  -0.0504   0.8939   0.4546
  -2.250  -0.0385   0.00643   0.00184  -0.0499   0.8867   0.5557
  -2.000  -0.0131   0.00623   0.00185  -0.0493   0.8788   0.6299
  -1.750   0.0127   0.00615   0.00185  -0.0485   0.8705   0.6742
  -1.500   0.0390   0.00612   0.00183  -0.0480   0.8606   0.7030
  -1.250   0.0656   0.00613   0.00183  -0.0474   0.8520   0.7268
  -1.000   0.0923   0.00614   0.00181  -0.0469   0.8432   0.7447
  -0.750   0.1189   0.00613   0.00179  -0.0464   0.8329   0.7605
  -0.500   0.1457   0.00615   0.00176  -0.0460   0.8227   0.7729
  -0.250   0.1726   0.00617   0.00173  -0.0455   0.8133   0.7847
   0.000   0.1995   0.00614   0.00172  -0.0452   0.8038   0.7958
   0.250   0.2264   0.00613   0.00172  -0.0448   0.7960   0.8090
   0.500   0.2531   0.00609   0.00172  -0.0443   0.7879   0.8233
   0.750   0.2798   0.00606   0.00172  -0.0439   0.7793   0.8364
   1.000   0.3061   0.00603   0.00172  -0.0433   0.7705   0.8510
   1.250   0.3322   0.00597   0.00174  -0.0427   0.7605   0.8683
   1.500   0.3580   0.00592   0.00175  -0.0421   0.7505   0.8868
   1.750   0.3835   0.00586   0.00175  -0.0413   0.7380   0.9086
   2.000   0.4109   0.00579   0.00170  -0.0409   0.7161   0.9375
   2.250   0.4480   0.00579   0.00165  -0.0427   0.6834   0.9727
   2.500   0.4816   0.00589   0.00165  -0.0440   0.6521   1.0000
   2.750   0.5078   0.00606   0.00170  -0.0437   0.6200   1.0000
   3.000   0.5335   0.00630   0.00179  -0.0433   0.5773   1.0000
   3.250   0.5574   0.00673   0.00190  -0.0426   0.5030   1.0000
   3.500   0.5810   0.00727   0.00210  -0.0420   0.4245   1.0000
   3.750   0.6053   0.00778   0.00233  -0.0416   0.3618   1.0000
   4.250   0.6550   0.00870   0.00284  -0.0409   0.2619   1.0000
   4.500   0.6801   0.00914   0.00310  -0.0406   0.2207   1.0000
   4.750   0.7049   0.00963   0.00340  -0.0403   0.1738   1.0000
   5.000   0.7268   0.01055   0.00388  -0.0396   0.0895   1.0000
   5.250   0.7505   0.01124   0.00439  -0.0391   0.0574   1.0000
   5.500   0.7755   0.01173   0.00485  -0.0386   0.0500   1.0000
   5.750   0.8009   0.01214   0.00530  -0.0383   0.0453   1.0000
   6.000   0.8261   0.01255   0.00574  -0.0379   0.0417   1.0000
   6.250   0.8500   0.01317   0.00639  -0.0374   0.0377   1.0000
   6.500   0.8746   0.01365   0.00695  -0.0369   0.0351   1.0000
   6.750   0.9004   0.01391   0.00726  -0.0367   0.0313   1.0000
   7.000   0.9234   0.01460   0.00797  -0.0361   0.0254   1.0000
   7.250   0.9483   0.01502   0.00837  -0.0357   0.0188   1.0000
   7.500   0.9718   0.01565   0.00907  -0.0350   0.0157   1.0000
   7.750   0.9952   0.01627   0.00971  -0.0344   0.0136   1.0000
   8.000   1.0136   0.01764   0.01119  -0.0331   0.0124   1.0000
   8.250   1.0359   0.01838   0.01203  -0.0323   0.0115   1.0000
   8.500   1.0577   0.01915   0.01289  -0.0315   0.0106   1.0000
   8.750   1.0781   0.02011   0.01393  -0.0305   0.0101   1.0000
   9.000   1.0975   0.02121   0.01513  -0.0295   0.0096   1.0000
   9.250   1.1147   0.02265   0.01670  -0.0282   0.0092   1.0000
   9.500   1.1282   0.02487   0.01916  -0.0265   0.0088   1.0000
   9.750   1.1371   0.02821   0.02285  -0.0244   0.0086   1.0000
  10.000   1.1500   0.03026   0.02517  -0.0227   0.0084   1.0000
  10.250   1.1590   0.03270   0.02790  -0.0208   0.0083   1.0000
  10.500   1.1625   0.03560   0.03112  -0.0184   0.0083   1.0000
  10.750   1.1594   0.03873   0.03456  -0.0156   0.0082   1.0000
  11.000   1.1466   0.04185   0.03797  -0.0118   0.0083   1.0000
  11.250   1.1300   0.04529   0.04166  -0.0089   0.0083   1.0000
  11.500   1.1111   0.04926   0.04586  -0.0072   0.0083   1.0000
  11.750   1.0897   0.05402   0.05084  -0.0070   0.0084   1.0000
  12.000   1.0695   0.05917   0.05619  -0.0082   0.0084   1.0000
  12.250   1.0439   0.06604   0.06325  -0.0114   0.0085   1.0000
  12.500   1.0316   0.07163   0.06897  -0.0146   0.0086   1.0000
  12.750   1.0114   0.07968   0.07718  -0.0203   0.0086   1.0000
  13.000   1.0022   0.08649   0.08410  -0.0253   0.0087   1.0000
  13.250   0.9800   0.09752   0.09527  -0.0332   0.0087   1.0000
  13.500   0.9666   0.10703   0.10488  -0.0395   0.0088   1.0000
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