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HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 AIRFOIL (hq259-il)
Reynolds number: 200,000
Max Cl/Cd: 73.01 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259-il-200000-n5.txt
Download as CSV file: xf-hq259-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4026   0.08810   0.08462  -0.0338   1.0000   0.0099
  -8.500  -0.4037   0.08465   0.08121  -0.0348   1.0000   0.0095
  -8.250  -0.4070   0.08072   0.07734  -0.0362   1.0000   0.0094
  -8.000  -0.4119   0.07720   0.07390  -0.0371   1.0000   0.0093
  -7.750  -0.4214   0.07388   0.07066  -0.0375   1.0000   0.0092
  -7.500  -0.4316   0.07053   0.06740  -0.0385   1.0000   0.0090
  -7.250  -0.4424   0.06625   0.06317  -0.0412   1.0000   0.0090
  -7.000  -0.4324   0.05989   0.05671  -0.0484   0.9949   0.0088
  -6.750  -0.4109   0.05260   0.04921  -0.0569   0.9872   0.0085
  -6.500  -0.3884   0.04536   0.04166  -0.0634   0.9797   0.0084
  -6.250  -0.3620   0.03837   0.03423  -0.0684   0.9741   0.0083
  -6.000  -0.3369   0.03238   0.02771  -0.0711   0.9674   0.0083
  -5.750  -0.3081   0.02705   0.02173  -0.0732   0.9624   0.0086
  -5.500  -0.2759   0.02439   0.01853  -0.0746   0.9585   0.0100
  -5.250  -0.2501   0.02109   0.01470  -0.0752   0.9519   0.0113
  -5.000  -0.2186   0.01901   0.01226  -0.0762   0.9478   0.0120
  -4.750  -0.1892   0.01743   0.01043  -0.0765   0.9426   0.0127
  -4.500  -0.1599   0.01613   0.00889  -0.0768   0.9370   0.0140
  -4.250  -0.1282   0.01502   0.00762  -0.0776   0.9329   0.0158
  -4.000  -0.1012   0.01423   0.00674  -0.0775   0.9258   0.0195
  -3.750  -0.0709   0.01345   0.00586  -0.0780   0.9208   0.0235
  -3.500  -0.0426   0.01278   0.00510  -0.0781   0.9144   0.0328
  -3.250  -0.0133   0.01235   0.00465  -0.0784   0.9085   0.0494
  -3.000   0.0153   0.01197   0.00434  -0.0788   0.9026   0.0772
  -2.750   0.0432   0.01156   0.00394  -0.0789   0.8957   0.1075
  -2.500   0.0709   0.01097   0.00361  -0.0791   0.8897   0.1912
  -2.250   0.0958   0.01011   0.00338  -0.0791   0.8822   0.3774
  -2.000   0.1210   0.00961   0.00335  -0.0787   0.8756   0.5322
  -1.750   0.1463   0.00942   0.00337  -0.0779   0.8681   0.6190
  -1.500   0.1725   0.00934   0.00332  -0.0772   0.8607   0.6657
  -1.250   0.1975   0.00926   0.00333  -0.0761   0.8530   0.7175
  -1.000   0.2216   0.00921   0.00335  -0.0749   0.8442   0.7582
  -0.750   0.2484   0.00916   0.00325  -0.0744   0.8367   0.7755
  -0.500   0.2749   0.00912   0.00316  -0.0739   0.8276   0.7875
  -0.250   0.3017   0.00909   0.00310  -0.0735   0.8194   0.7996
   0.000   0.3286   0.00905   0.00303  -0.0731   0.8115   0.8124
   0.250   0.3548   0.00902   0.00299  -0.0726   0.8014   0.8262
   0.500   0.3808   0.00896   0.00291  -0.0720   0.7895   0.8414
   0.750   0.4066   0.00890   0.00283  -0.0712   0.7756   0.8588
   1.000   0.4330   0.00884   0.00277  -0.0706   0.7622   0.8799
   1.250   0.4620   0.00878   0.00273  -0.0706   0.7501   0.9088
   1.500   0.4992   0.00872   0.00269  -0.0725   0.7372   0.9620
   1.750   0.5294   0.00877   0.00269  -0.0730   0.7232   1.0000
   2.000   0.5563   0.00886   0.00271  -0.0728   0.7075   1.0000
   2.250   0.5831   0.00896   0.00275  -0.0726   0.6903   1.0000
   2.500   0.6097   0.00908   0.00284  -0.0723   0.6720   1.0000
   2.750   0.6360   0.00921   0.00291  -0.0719   0.6517   1.0000
   3.000   0.6620   0.00937   0.00301  -0.0715   0.6285   1.0000
   3.250   0.6875   0.00956   0.00311  -0.0710   0.5995   1.0000
   3.500   0.7123   0.00980   0.00323  -0.0704   0.5660   1.0000
   3.750   0.7367   0.01009   0.00343  -0.0697   0.5281   1.0000
   4.000   0.7602   0.01046   0.00364  -0.0689   0.4866   1.0000
   4.250   0.7831   0.01090   0.00390  -0.0681   0.4435   1.0000
   4.500   0.8057   0.01138   0.00422  -0.0673   0.4002   1.0000
   4.750   0.8282   0.01190   0.00457  -0.0665   0.3565   1.0000
   5.000   0.8504   0.01245   0.00502  -0.0657   0.3148   1.0000
   5.250   0.8731   0.01298   0.00544  -0.0650   0.2825   1.0000
   5.500   0.8964   0.01347   0.00588  -0.0643   0.2578   1.0000
   5.750   0.9168   0.01422   0.00638  -0.0634   0.2077   1.0000
   6.000   0.9363   0.01511   0.00691  -0.0625   0.1491   1.0000
   6.250   0.9581   0.01576   0.00746  -0.0617   0.1195   1.0000
   6.500   0.9774   0.01673   0.00815  -0.0607   0.0734   1.0000
   6.750   0.9925   0.01825   0.00929  -0.0592   0.0171   1.0000
   7.000   1.0129   0.01916   0.01025  -0.0580   0.0105   1.0000
   7.250   1.0336   0.02000   0.01124  -0.0569   0.0088   1.0000
   7.500   1.0515   0.02118   0.01256  -0.0555   0.0066   1.0000
   7.750   1.0712   0.02206   0.01360  -0.0543   0.0060   1.0000
   8.000   1.0889   0.02315   0.01488  -0.0529   0.0056   1.0000
   8.250   1.1051   0.02433   0.01624  -0.0513   0.0053   1.0000
   8.500   1.1193   0.02568   0.01776  -0.0495   0.0051   1.0000
   8.750   1.1322   0.02710   0.01935  -0.0476   0.0049   1.0000
   9.000   1.1440   0.02863   0.02104  -0.0455   0.0048   1.0000
   9.250   1.1540   0.03029   0.02286  -0.0433   0.0047   1.0000
   9.500   1.1627   0.03200   0.02481  -0.0409   0.0046   1.0000
   9.750   1.1702   0.03392   0.02692  -0.0385   0.0045   1.0000
  10.000   1.1770   0.03593   0.02914  -0.0363   0.0045   1.0000
  10.250   1.1821   0.03816   0.03159  -0.0340   0.0045   1.0000
  10.500   1.1851   0.04056   0.03423  -0.0318   0.0045   1.0000
  10.750   1.1856   0.04316   0.03709  -0.0297   0.0045   1.0000
  11.000   1.1830   0.04603   0.04022  -0.0278   0.0044   1.0000
  11.250   1.1789   0.04911   0.04356  -0.0262   0.0045   1.0000
  11.500   1.1711   0.05263   0.04735  -0.0250   0.0045   1.0000
  11.750   1.1611   0.05657   0.05155  -0.0245   0.0045   1.0000
  12.000   1.1498   0.06085   0.05607  -0.0246   0.0045   1.0000
  12.250   1.1357   0.06585   0.06131  -0.0256   0.0045   1.0000
  12.500   1.1221   0.07113   0.06682  -0.0274   0.0046   1.0000
  12.750   1.1050   0.07751   0.07342  -0.0304   0.0046   1.0000
  13.000   1.0873   0.08469   0.08081  -0.0344   0.0046   1.0000
  13.250   1.0704   0.09247   0.08877  -0.0392   0.0047   1.0000
  13.500   1.0522   0.10138   0.09786  -0.0450   0.0047   1.0000
  13.750   1.0342   0.11118   0.10782  -0.0514   0.0048   1.0000
  14.000   1.0147   0.12211   0.11888  -0.0582   0.0048   1.0000
  14.250   0.9942   0.13416   0.13103  -0.0653   0.0049   1.0000
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