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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 100,000
Max Cl/Cd: 55.92 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2510-il-100000-n5.txt
Download as CSV file: xf-hq2510-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/10 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4083   0.08885   0.08402  -0.0385   1.0000   0.0213
  -8.750  -0.4192   0.08206   0.07736  -0.0425   1.0000   0.0199
  -8.250  -0.4314   0.07222   0.06765  -0.0478   1.0000   0.0191
  -8.000  -0.4453   0.06840   0.06390  -0.0490   1.0000   0.0189
  -7.750  -0.4572   0.06460   0.06012  -0.0498   1.0000   0.0188
  -7.500  -0.4693   0.06110   0.05660  -0.0494   1.0000   0.0187
  -7.250  -0.4799   0.05777   0.05321  -0.0483   1.0000   0.0185
  -7.000  -0.4884   0.05422   0.04953  -0.0472   1.0000   0.0185
  -6.750  -0.4857   0.04963   0.04469  -0.0482   0.9978   0.0184
  -6.500  -0.4636   0.04347   0.03801  -0.0528   0.9907   0.0184
  -6.250  -0.4372   0.03802   0.03191  -0.0564   0.9849   0.0187
  -6.000  -0.4124   0.03392   0.02729  -0.0586   0.9785   0.0201
  -5.750  -0.3816   0.03211   0.02524  -0.0610   0.9737   0.0225
  -5.500  -0.3524   0.02919   0.02181  -0.0622   0.9682   0.0240
  -5.250  -0.3216   0.02634   0.01841  -0.0631   0.9632   0.0254
  -5.000  -0.2875   0.02403   0.01559  -0.0643   0.9596   0.0275
  -4.750  -0.2583   0.02233   0.01366  -0.0648   0.9540   0.0310
  -4.500  -0.2264   0.02133   0.01254  -0.0659   0.9490   0.0376
  -4.250  -0.1923   0.01988   0.01100  -0.0673   0.9455   0.0449
  -4.000  -0.1640   0.01912   0.01018  -0.0677   0.9390   0.0580
  -3.750  -0.1312   0.01839   0.00941  -0.0689   0.9342   0.0744
  -3.500  -0.0984   0.01771   0.00863  -0.0701   0.9297   0.0920
  -3.250  -0.0704   0.01706   0.00799  -0.0704   0.9229   0.1113
  -3.000  -0.0372   0.01626   0.00739  -0.0718   0.9186   0.1643
  -2.750  -0.0134   0.01497   0.00706  -0.0720   0.9117   0.3785
  -2.500   0.0136   0.01446   0.00718  -0.0716   0.9063   0.5720
  -2.250   0.0408   0.01441   0.00717  -0.0709   0.9002   0.6420
  -2.000   0.0676   0.01441   0.00717  -0.0702   0.8936   0.6898
  -1.750   0.0937   0.01441   0.00721  -0.0690   0.8881   0.7407
  -1.500   0.1156   0.01442   0.00724  -0.0670   0.8804   0.7805
  -1.250   0.1441   0.01434   0.00707  -0.0665   0.8751   0.8064
  -1.000   0.1692   0.01428   0.00696  -0.0657   0.8670   0.8228
  -0.750   0.2008   0.01416   0.00674  -0.0661   0.8616   0.8363
  -0.500   0.2266   0.01410   0.00664  -0.0656   0.8530   0.8507
  -0.250   0.2569   0.01398   0.00645  -0.0657   0.8467   0.8655
   0.000   0.2848   0.01390   0.00636  -0.0655   0.8383   0.8823
   0.250   0.3165   0.01381   0.00624  -0.0661   0.8311   0.9015
   0.500   0.3527   0.01371   0.00613  -0.0676   0.8236   0.9228
   0.750   0.3922   0.01364   0.00605  -0.0700   0.8158   0.9516
   1.000   0.4340   0.01352   0.00589  -0.0728   0.8078   1.0000
   1.250   0.4598   0.01351   0.00582  -0.0724   0.7952   1.0000
   1.500   0.4864   0.01347   0.00571  -0.0721   0.7818   1.0000
   1.750   0.5131   0.01347   0.00565  -0.0718   0.7687   1.0000
   2.000   0.5398   0.01352   0.00567  -0.0715   0.7567   1.0000
   2.250   0.5667   0.01357   0.00573  -0.0712   0.7446   1.0000
   2.500   0.5936   0.01362   0.00576  -0.0709   0.7316   1.0000
   2.750   0.6202   0.01367   0.00580  -0.0705   0.7172   1.0000
   3.000   0.6466   0.01373   0.00585  -0.0700   0.7015   1.0000
   3.250   0.6732   0.01379   0.00593  -0.0696   0.6847   1.0000
   3.500   0.6991   0.01388   0.00603  -0.0690   0.6660   1.0000
   3.750   0.7246   0.01399   0.00614  -0.0683   0.6453   1.0000
   4.000   0.7498   0.01411   0.00627  -0.0676   0.6219   1.0000
   4.250   0.7745   0.01427   0.00640  -0.0668   0.5945   1.0000
   4.500   0.7987   0.01447   0.00660  -0.0659   0.5625   1.0000
   4.750   0.8222   0.01474   0.00678  -0.0649   0.5258   1.0000
   5.000   0.8449   0.01511   0.00702  -0.0638   0.4858   1.0000
   5.250   0.8666   0.01558   0.00734  -0.0627   0.4448   1.0000
   5.500   0.8875   0.01614   0.00775  -0.0615   0.4048   1.0000
   5.750   0.9081   0.01676   0.00829  -0.0603   0.3665   1.0000
   6.000   0.9284   0.01741   0.00883  -0.0592   0.3314   1.0000
   6.250   0.9484   0.01811   0.00943  -0.0581   0.3003   1.0000
   6.500   0.9686   0.01881   0.01007  -0.0570   0.2739   1.0000
   6.750   0.9887   0.01952   0.01076  -0.0559   0.2509   1.0000
   7.000   1.0090   0.02022   0.01150  -0.0549   0.2295   1.0000
   7.250   1.0283   0.02097   0.01223  -0.0538   0.2047   1.0000
   7.500   1.0466   0.02176   0.01303  -0.0526   0.1771   1.0000
   7.750   1.0649   0.02258   0.01384  -0.0514   0.1563   1.0000
   8.000   1.0835   0.02339   0.01469  -0.0502   0.1357   1.0000
   8.250   1.0977   0.02456   0.01554  -0.0489   0.0920   1.0000
   8.500   1.1091   0.02617   0.01676  -0.0472   0.0435   1.0000
   8.750   1.1186   0.02800   0.01840  -0.0450   0.0226   1.0000
   9.000   1.1303   0.02950   0.02004  -0.0430   0.0181   1.0000
   9.250   1.1384   0.03114   0.02181  -0.0406   0.0158   1.0000
   9.500   1.1430   0.03292   0.02376  -0.0378   0.0145   1.0000
   9.750   1.1489   0.03454   0.02560  -0.0353   0.0139   1.0000
  10.000   1.1532   0.03631   0.02759  -0.0330   0.0135   1.0000
  10.250   1.1554   0.03832   0.02989  -0.0307   0.0129   1.0000
  10.500   1.1573   0.04043   0.03222  -0.0286   0.0126   1.0000
  10.750   1.1589   0.04269   0.03469  -0.0268   0.0123   1.0000
  11.000   1.1595   0.04521   0.03740  -0.0252   0.0119   1.0000
  11.250   1.1600   0.04783   0.04022  -0.0239   0.0116   1.0000
  11.500   1.1597   0.05062   0.04323  -0.0229   0.0112   1.0000
  11.750   1.1576   0.05362   0.04640  -0.0222   0.0106   1.0000
  12.000   1.1550   0.05686   0.04986  -0.0218   0.0104   1.0000
  12.250   1.1499   0.06046   0.05364  -0.0219   0.0101   1.0000
  12.500   1.1428   0.06447   0.05784  -0.0224   0.0097   1.0000
  12.750   1.1339   0.06895   0.06251  -0.0234   0.0095   1.0000
  13.000   1.1234   0.07395   0.06770  -0.0249   0.0093   1.0000
  13.250   1.1151   0.07895   0.07293  -0.0266   0.0094   1.0000
  13.500   1.1011   0.08506   0.07924  -0.0294   0.0092   1.0000
  13.750   1.0873   0.09161   0.08599  -0.0327   0.0091   1.0000
  14.000   1.0737   0.09862   0.09320  -0.0367   0.0091   1.0000
  14.250   1.0615   0.10593   0.10072  -0.0410   0.0093   1.0000
  14.500   1.0460   0.11433   0.10930  -0.0461   0.0093   1.0000
  14.750   1.0296   0.12384   0.11903  -0.0519   0.0097   1.0000
  15.000   0.9996   0.13834   0.13382  -0.0604   0.0108   1.0000
  15.250   0.9737   0.15241   0.14800  -0.0682   0.0118   1.0000
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