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HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/8 AIRFOIL (hq258-il)
Reynolds number: 500,000
Max Cl/Cd: 90.54 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq258-il-500000-n5.txt
Download as CSV file: xf-hq258-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3916   0.08390   0.08172  -0.0312   1.0000   0.0079
  -7.750  -0.3927   0.08067   0.07854  -0.0320   1.0000   0.0079
  -7.500  -0.3978   0.07766   0.07557  -0.0322   1.0000   0.0079
  -7.000  -0.3822   0.06825   0.06621  -0.0431   0.9915   0.0079
  -6.750  -0.3571   0.06110   0.05898  -0.0542   0.9850   0.0079
  -6.500  -0.3335   0.05475   0.05251  -0.0621   0.9778   0.0079
  -6.250  -0.3179   0.04555   0.04308  -0.0714   0.9687   0.0062
  -6.000  -0.2914   0.03945   0.03672  -0.0764   0.9614   0.0055
  -5.750  -0.2671   0.03267   0.02954  -0.0793   0.9516   0.0048
  -5.500  -0.2426   0.02337   0.01953  -0.0800   0.9419   0.0038
  -5.250  -0.2163   0.02028   0.01601  -0.0803   0.9346   0.0037
  -5.000  -0.1909   0.01793   0.01328  -0.0801   0.9265   0.0036
  -4.750  -0.1646   0.01587   0.01083  -0.0800   0.9197   0.0036
  -4.500  -0.1390   0.01374   0.00832  -0.0795   0.9119   0.0037
  -4.250  -0.1130   0.01216   0.00645  -0.0790   0.9052   0.0038
  -4.000  -0.0872   0.01096   0.00505  -0.0786   0.8977   0.0042
  -3.750  -0.0606   0.01030   0.00428  -0.0783   0.8910   0.0048
  -3.500  -0.0337   0.00980   0.00364  -0.0781   0.8836   0.0057
  -3.250  -0.0066   0.00943   0.00317  -0.0779   0.8768   0.0072
  -3.000   0.0205   0.00903   0.00266  -0.0777   0.8697   0.0101
  -2.750   0.0480   0.00868   0.00224  -0.0775   0.8627   0.0154
  -2.500   0.0753   0.00840   0.00200  -0.0774   0.8554   0.0367
  -2.250   0.1027   0.00823   0.00181  -0.0773   0.8480   0.0528
  -2.000   0.1299   0.00803   0.00165  -0.0772   0.8400   0.0822
  -1.750   0.1565   0.00755   0.00146  -0.0773   0.8301   0.1880
  -1.500   0.1830   0.00706   0.00131  -0.0773   0.8204   0.3175
  -1.250   0.2093   0.00662   0.00122  -0.0773   0.8114   0.4574
  -1.000   0.2361   0.00640   0.00119  -0.0771   0.8022   0.5364
  -0.750   0.2624   0.00622   0.00119  -0.0768   0.7923   0.6188
  -0.500   0.2879   0.00608   0.00123  -0.0761   0.7796   0.6960
  -0.250   0.3138   0.00604   0.00123  -0.0756   0.7641   0.7344
   0.000   0.3406   0.00607   0.00121  -0.0752   0.7485   0.7480
   0.250   0.3677   0.00610   0.00119  -0.0750   0.7344   0.7590
   0.500   0.3947   0.00613   0.00119  -0.0748   0.7202   0.7704
   0.750   0.4215   0.00617   0.00119  -0.0745   0.7044   0.7822
   1.000   0.4481   0.00622   0.00121  -0.0741   0.6864   0.7949
   1.250   0.4744   0.00627   0.00124  -0.0738   0.6682   0.8090
   1.500   0.5005   0.00633   0.00129  -0.0734   0.6497   0.8252
   1.750   0.5261   0.00638   0.00133  -0.0728   0.6287   0.8447
   2.000   0.5505   0.00643   0.00138  -0.0720   0.6023   0.8717
   2.250   0.5774   0.00648   0.00143  -0.0717   0.5663   0.9375
   2.500   0.6084   0.00672   0.00152  -0.0725   0.5257   1.0000
   2.750   0.6336   0.00703   0.00168  -0.0721   0.4844   1.0000
   3.000   0.6587   0.00737   0.00185  -0.0718   0.4420   1.0000
   3.250   0.6840   0.00771   0.00203  -0.0714   0.4040   1.0000
   3.500   0.7088   0.00811   0.00225  -0.0710   0.3593   1.0000
   3.750   0.7328   0.00860   0.00250  -0.0706   0.3046   1.0000
   4.000   0.7544   0.00940   0.00285  -0.0699   0.2197   1.0000
   4.250   0.7785   0.00991   0.00318  -0.0694   0.1718   1.0000
   4.500   0.8032   0.01034   0.00347  -0.0691   0.1408   1.0000
   4.750   0.8265   0.01097   0.00386  -0.0685   0.0924   1.0000
   5.000   0.8452   0.01224   0.00463  -0.0674   0.0089   1.0000
   5.250   0.8701   0.01267   0.00507  -0.0669   0.0041   1.0000
   5.500   0.8952   0.01308   0.00556  -0.0665   0.0034   1.0000
   5.750   0.9197   0.01356   0.00613  -0.0659   0.0029   1.0000
   6.000   0.9437   0.01411   0.00684  -0.0653   0.0026   1.0000
   6.250   0.9669   0.01480   0.00766  -0.0645   0.0023   1.0000
   6.500   0.9889   0.01564   0.00863  -0.0635   0.0022   1.0000
   6.750   1.0101   0.01657   0.00968  -0.0625   0.0021   1.0000
   7.000   1.0300   0.01766   0.01090  -0.0612   0.0021   1.0000
   7.250   1.0492   0.01882   0.01219  -0.0599   0.0021   1.0000
   7.500   1.0678   0.02010   0.01360  -0.0585   0.0021   1.0000
   7.750   1.0863   0.02145   0.01509  -0.0571   0.0021   1.0000
   8.000   1.1042   0.02296   0.01676  -0.0556   0.0021   1.0000
   8.250   1.1222   0.02446   0.01843  -0.0543   0.0021   1.0000
   8.500   1.1393   0.02616   0.02033  -0.0528   0.0021   1.0000
   8.750   1.1552   0.02802   0.02241  -0.0512   0.0022   1.0000
   9.000   1.1692   0.03011   0.02481  -0.0494   0.0022   1.0000
   9.250   1.1804   0.03251   0.02751  -0.0473   0.0023   1.0000
   9.500   1.1876   0.03531   0.03065  -0.0448   0.0024   1.0000
   9.750   1.1890   0.03865   0.03434  -0.0418   0.0025   1.0000
  10.000   1.1824   0.04199   0.03802  -0.0380   0.0026   1.0000
  10.250   1.1688   0.04537   0.04169  -0.0339   0.0027   1.0000
  10.500   1.1536   0.04888   0.04547  -0.0307   0.0028   1.0000
  10.750   1.1373   0.05274   0.04955  -0.0288   0.0029   1.0000
  11.000   1.1208   0.05696   0.05398  -0.0280   0.0029   1.0000
  11.250   1.1012   0.06214   0.05937  -0.0286   0.0030   1.0000
  11.500   1.0833   0.06774   0.06514  -0.0306   0.0030   1.0000
  11.750   1.0643   0.07441   0.07198  -0.0342   0.0030   1.0000
  12.000   1.0495   0.08132   0.07902  -0.0388   0.0030   1.0000
  12.250   1.0316   0.09032   0.08817  -0.0453   0.0030   1.0000
  12.500   1.0144   0.10075   0.09871  -0.0526   0.0029   1.0000
  12.750   0.9967   0.11243   0.11048  -0.0599   0.0029   1.0000
  13.000   0.9777   0.12498   0.12308  -0.0666   0.0029   1.0000
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