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HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/8 AIRFOIL (hq208-il)
Reynolds number: 100,000
Max Cl/Cd: 53.83 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq208-il-100000-n5.txt
Download as CSV file: xf-hq208-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/8 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3676   0.09229   0.08762  -0.0233   1.0000   0.0261
  -9.000  -0.3733   0.08657   0.08193  -0.0268   1.0000   0.0209
  -8.750  -0.3735   0.08233   0.07773  -0.0278   1.0000   0.0206
  -8.500  -0.4539   0.08973   0.08484  -0.0263   1.0000   0.0206
  -8.250  -0.4528   0.08608   0.08124  -0.0271   1.0000   0.0199
  -8.000  -0.4536   0.08219   0.07743  -0.0289   1.0000   0.0196
  -7.750  -0.4561   0.07845   0.07376  -0.0305   1.0000   0.0191
  -7.500  -0.4579   0.07422   0.06960  -0.0336   1.0000   0.0187
  -7.250  -0.4578   0.06924   0.06465  -0.0380   1.0000   0.0183
  -7.000  -0.4565   0.06466   0.06004  -0.0408   1.0000   0.0179
  -6.750  -0.4542   0.06014   0.05546  -0.0428   1.0000   0.0176
  -6.500  -0.4501   0.05580   0.05101  -0.0442   1.0000   0.0177
  -6.250  -0.4440   0.05163   0.04668  -0.0449   1.0000   0.0178
  -6.000  -0.4361   0.04756   0.04239  -0.0451   1.0000   0.0183
  -5.750  -0.4262   0.04378   0.03834  -0.0448   1.0000   0.0186
  -5.500  -0.4140   0.04011   0.03434  -0.0442   1.0000   0.0194
  -5.250  -0.3997   0.03672   0.03054  -0.0434   1.0000   0.0199
  -5.000  -0.3837   0.03334   0.02673  -0.0425   1.0000   0.0199
  -4.750  -0.3653   0.03027   0.02320  -0.0417   1.0000   0.0200
  -4.500  -0.3450   0.02755   0.01999  -0.0407   1.0000   0.0202
  -4.250  -0.3119   0.02480   0.01660  -0.0419   0.9964   0.0207
  -4.000  -0.2778   0.02264   0.01398  -0.0430   0.9923   0.0215
  -3.750  -0.2455   0.02050   0.01170  -0.0443   0.9881   0.0251
  -3.500  -0.2115   0.01933   0.01033  -0.0456   0.9838   0.0302
  -3.250  -0.1793   0.01806   0.00888  -0.0463   0.9785   0.0333
  -3.000  -0.1453   0.01684   0.00760  -0.0478   0.9741   0.0421
  -2.750  -0.1133   0.01599   0.00676  -0.0489   0.9682   0.0721
  -2.500  -0.0809   0.01473   0.00605  -0.0506   0.9631   0.1843
  -2.250  -0.0525   0.01318   0.00592  -0.0515   0.9586   0.5448
  -2.000  -0.0257   0.01296   0.00596  -0.0507   0.9514   0.6756
  -1.750   0.0055   0.01285   0.00593  -0.0506   0.9465   0.7554
  -1.500   0.0273   0.01269   0.00589  -0.0483   0.9385   0.8268
  -1.250   0.0583   0.01249   0.00569  -0.0479   0.9337   0.8894
  -1.000   0.0983   0.01238   0.00549  -0.0501   0.9279   0.9257
  -0.750   0.1453   0.01230   0.00527  -0.0542   0.9232   0.9603
  -0.500   0.1904   0.01223   0.00503  -0.0580   0.9181   1.0000
  -0.250   0.2219   0.01224   0.00492  -0.0591   0.9090   1.0000
   0.000   0.2537   0.01227   0.00484  -0.0601   0.9003   1.0000
   0.250   0.2880   0.01227   0.00475  -0.0615   0.8928   1.0000
   0.500   0.3170   0.01232   0.00474  -0.0618   0.8823   1.0000
   0.750   0.3469   0.01233   0.00470  -0.0621   0.8712   1.0000
   1.000   0.3766   0.01231   0.00462  -0.0622   0.8579   1.0000
   1.250   0.4053   0.01227   0.00453  -0.0619   0.8422   1.0000
   1.500   0.4332   0.01223   0.00449  -0.0615   0.8259   1.0000
   1.750   0.4603   0.01224   0.00447  -0.0610   0.8104   1.0000
   2.000   0.4867   0.01230   0.00454  -0.0605   0.7955   1.0000
   2.250   0.5131   0.01236   0.00462  -0.0600   0.7802   1.0000
   2.500   0.5395   0.01242   0.00471  -0.0595   0.7637   1.0000
   2.750   0.5661   0.01249   0.00485  -0.0589   0.7464   1.0000
   3.000   0.5924   0.01256   0.00496  -0.0583   0.7272   1.0000
   3.250   0.6183   0.01265   0.00509  -0.0576   0.7051   1.0000
   3.500   0.6440   0.01275   0.00523  -0.0568   0.6798   1.0000
   3.750   0.6695   0.01289   0.00537  -0.0559   0.6498   1.0000
   4.000   0.6943   0.01307   0.00561  -0.0550   0.6125   1.0000
   4.250   0.7181   0.01334   0.00579  -0.0538   0.5630   1.0000
   4.500   0.7398   0.01380   0.00598  -0.0523   0.4916   1.0000
   4.750   0.7592   0.01456   0.00631  -0.0507   0.4065   1.0000
   5.000   0.7788   0.01541   0.00679  -0.0494   0.3320   1.0000
   5.250   0.7997   0.01622   0.00737  -0.0484   0.2795   1.0000
   5.500   0.8217   0.01694   0.00809  -0.0476   0.2409   1.0000
   5.750   0.8435   0.01772   0.00877  -0.0469   0.1916   1.0000
   6.000   0.8635   0.01876   0.00952  -0.0460   0.1290   1.0000
   6.250   0.8832   0.01995   0.01052  -0.0449   0.0946   1.0000
   6.500   0.9033   0.02111   0.01169  -0.0438   0.0766   1.0000
   6.750   0.9234   0.02220   0.01272  -0.0430   0.0573   1.0000
   7.000   0.9429   0.02340   0.01392  -0.0421   0.0432   1.0000
   7.250   0.9624   0.02463   0.01528  -0.0410   0.0307   1.0000
   7.500   0.9803   0.02613   0.01687  -0.0397   0.0203   1.0000
   7.750   0.9968   0.02788   0.01900  -0.0380   0.0172   1.0000
   8.000   1.0130   0.02976   0.02109  -0.0364   0.0150   1.0000
   8.250   1.0288   0.03175   0.02327  -0.0350   0.0136   1.0000
   8.500   1.0426   0.03432   0.02607  -0.0334   0.0126   1.0000
   8.750   1.0548   0.03776   0.02982  -0.0317   0.0120   1.0000
   9.000   1.0670   0.04084   0.03331  -0.0300   0.0117   1.0000
   9.250   1.0748   0.04425   0.03717  -0.0281   0.0115   1.0000
   9.500   1.0776   0.04777   0.04113  -0.0259   0.0113   1.0000
   9.750   1.0750   0.05136   0.04514  -0.0237   0.0110   1.0000
  10.000   1.0661   0.05477   0.04888  -0.0211   0.0109   1.0000
  10.250   1.0529   0.05836   0.05276  -0.0189   0.0109   1.0000
  10.500   1.0372   0.06232   0.05700  -0.0179   0.0106   1.0000
  10.750   1.0199   0.06691   0.06183  -0.0183   0.0105   1.0000
  11.000   1.0019   0.07218   0.06729  -0.0201   0.0108   1.0000
  11.250   0.9828   0.07847   0.07375  -0.0235   0.0110   1.0000
  11.500   0.9644   0.08567   0.08108  -0.0283   0.0113   1.0000
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