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HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il)
Reynolds number: 500,000
Max Cl/Cd: 109.37 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3012-il-500000.txt
Download as CSV file: xf-hq3012-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/12 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5020   0.04640   0.04398  -0.0819   0.9857   0.0156
  -9.000  -0.5095   0.03488   0.03177  -0.0906   0.9753   0.0138
  -8.750  -0.4999   0.02573   0.02164  -0.0955   0.9698   0.0133
  -8.500  -0.4802   0.02270   0.01815  -0.0960   0.9618   0.0136
  -8.250  -0.4532   0.02046   0.01557  -0.0971   0.9571   0.0140
  -8.000  -0.4291   0.01897   0.01382  -0.0970   0.9500   0.0144
  -7.750  -0.4033   0.01777   0.01241  -0.0970   0.9436   0.0147
  -7.500  -0.3805   0.01629   0.01072  -0.0965   0.9363   0.0152
  -7.250  -0.3575   0.01513   0.00945  -0.0960   0.9291   0.0160
  -7.000  -0.3321   0.01467   0.00894  -0.0957   0.9224   0.0171
  -6.750  -0.3071   0.01415   0.00835  -0.0952   0.9152   0.0183
  -6.500  -0.2817   0.01362   0.00769  -0.0948   0.9088   0.0194
  -6.250  -0.2589   0.01270   0.00672  -0.0940   0.9012   0.0211
  -6.000  -0.2328   0.01233   0.00629  -0.0937   0.8951   0.0235
  -5.750  -0.2082   0.01178   0.00568  -0.0932   0.8877   0.0274
  -5.250  -0.1551   0.01129   0.00517  -0.0927   0.8749   0.0406
  -5.000  -0.1287   0.01096   0.00477  -0.0924   0.8690   0.0460
  -4.750  -0.1020   0.01076   0.00454  -0.0923   0.8625   0.0507
  -4.500  -0.0747   0.01065   0.00437  -0.0921   0.8563   0.0541
  -4.250  -0.0484   0.01026   0.00397  -0.0919   0.8505   0.0617
  -4.000  -0.0213   0.01011   0.00377  -0.0918   0.8439   0.0676
  -3.750   0.0056   0.00977   0.00342  -0.0916   0.8384   0.0774
  -3.500   0.0323   0.00948   0.00316  -0.0914   0.8318   0.0916
  -3.250   0.0589   0.00910   0.00289  -0.0913   0.8258   0.1284
  -3.000   0.0843   0.00848   0.00265  -0.0913   0.8197   0.2392
  -2.750   0.1084   0.00766   0.00243  -0.0911   0.8128   0.4137
  -2.500   0.1346   0.00738   0.00238  -0.0908   0.8066   0.5122
  -2.250   0.1616   0.00728   0.00236  -0.0906   0.7994   0.5566
  -2.000   0.1895   0.00726   0.00233  -0.0904   0.7937   0.5866
  -1.750   0.2169   0.00724   0.00234  -0.0902   0.7869   0.6082
  -1.500   0.2449   0.00726   0.00232  -0.0900   0.7811   0.6281
  -1.250   0.2727   0.00728   0.00232  -0.0899   0.7751   0.6439
  -1.000   0.3005   0.00728   0.00232  -0.0898   0.7686   0.6570
  -0.750   0.3278   0.00732   0.00235  -0.0894   0.7618   0.6768
  -0.500   0.3549   0.00733   0.00236  -0.0891   0.7533   0.6915
  -0.250   0.3825   0.00735   0.00235  -0.0889   0.7451   0.7006
   0.000   0.4100   0.00736   0.00235  -0.0887   0.7376   0.7104
   0.250   0.4376   0.00739   0.00237  -0.0886   0.7307   0.7211
   0.500   0.4652   0.00740   0.00237  -0.0884   0.7234   0.7291
   0.750   0.4930   0.00742   0.00238  -0.0883   0.7160   0.7360
   1.000   0.5205   0.00743   0.00238  -0.0882   0.7081   0.7429
   1.250   0.5480   0.00745   0.00239  -0.0880   0.6990   0.7505
   1.500   0.5750   0.00747   0.00240  -0.0878   0.6893   0.7578
   1.750   0.6022   0.00749   0.00242  -0.0876   0.6789   0.7656
   2.000   0.6292   0.00751   0.00246  -0.0873   0.6691   0.7735
   2.250   0.6562   0.00756   0.00249  -0.0871   0.6595   0.7818
   2.500   0.6829   0.00760   0.00254  -0.0868   0.6487   0.7908
   2.750   0.7094   0.00762   0.00260  -0.0865   0.6367   0.7997
   3.000   0.7357   0.00767   0.00265  -0.0861   0.6239   0.8099
   3.250   0.7615   0.00772   0.00272  -0.0856   0.6093   0.8208
   3.500   0.7867   0.00778   0.00279  -0.0851   0.5926   0.8327
   4.000   0.8351   0.00793   0.00296  -0.0835   0.5531   0.8642
   4.250   0.8569   0.00802   0.00307  -0.0822   0.5292   0.8917
   4.500   0.8903   0.00814   0.00320  -0.0835   0.4976   1.0000
   4.750   0.9143   0.00846   0.00338  -0.0829   0.4682   1.0000
   5.000   0.9373   0.00883   0.00362  -0.0822   0.4371   1.0000
   5.250   0.9600   0.00923   0.00387  -0.0814   0.4069   1.0000
   5.500   0.9824   0.00962   0.00414  -0.0806   0.3783   1.0000
   5.750   1.0045   0.01004   0.00443  -0.0797   0.3489   1.0000
   6.000   1.0261   0.01049   0.00475  -0.0788   0.3211   1.0000
   6.500   1.0689   0.01137   0.00541  -0.0769   0.2741   1.0000
   6.750   1.0901   0.01182   0.00576  -0.0759   0.2538   1.0000
   7.000   1.1114   0.01224   0.00613  -0.0750   0.2359   1.0000
   7.250   1.1328   0.01264   0.00648  -0.0740   0.2188   1.0000
   7.500   1.1536   0.01307   0.00685  -0.0730   0.2028   1.0000
   7.750   1.1732   0.01355   0.00724  -0.0718   0.1850   1.0000
   8.000   1.1924   0.01403   0.00766  -0.0705   0.1694   1.0000
   8.250   1.2111   0.01452   0.00810  -0.0692   0.1549   1.0000
   8.500   1.2294   0.01499   0.00853  -0.0678   0.1417   1.0000
   8.750   1.2468   0.01543   0.00896  -0.0661   0.1312   1.0000
   9.000   1.2627   0.01593   0.00943  -0.0643   0.1200   1.0000
   9.250   1.2777   0.01649   0.00994  -0.0624   0.1081   1.0000
   9.500   1.2920   0.01709   0.01052  -0.0605   0.0959   1.0000
   9.750   1.3056   0.01776   0.01113  -0.0585   0.0843   1.0000
  10.000   1.3182   0.01849   0.01182  -0.0564   0.0721   1.0000
  10.500   1.3425   0.02007   0.01333  -0.0525   0.0538   1.0000
  10.750   1.3548   0.02088   0.01415  -0.0507   0.0476   1.0000
  11.250   1.3779   0.02264   0.01595  -0.0471   0.0370   1.0000
  11.500   1.3875   0.02371   0.01700  -0.0453   0.0318   1.0000
  11.750   1.3990   0.02466   0.01799  -0.0437   0.0275   1.0000
  12.000   1.4068   0.02591   0.01924  -0.0419   0.0213   1.0000
  12.250   1.4130   0.02733   0.02066  -0.0400   0.0160   1.0000
  12.500   1.4177   0.02892   0.02227  -0.0382   0.0119   1.0000
  12.750   1.4217   0.03064   0.02402  -0.0365   0.0097   1.0000
  13.000   1.4268   0.03231   0.02578  -0.0350   0.0085   1.0000
  13.250   1.4308   0.03414   0.02770  -0.0336   0.0078   1.0000
  13.500   1.4335   0.03615   0.02981  -0.0323   0.0074   1.0000
  13.750   1.4346   0.03839   0.03216  -0.0312   0.0071   1.0000
  14.000   1.4363   0.04064   0.03454  -0.0302   0.0068   1.0000
  14.250   1.4373   0.04304   0.03706  -0.0294   0.0067   1.0000
  14.500   1.4366   0.04573   0.03987  -0.0289   0.0066   1.0000
  14.750   1.4346   0.04868   0.04295  -0.0285   0.0064   1.0000
  15.000   1.4320   0.05183   0.04622  -0.0284   0.0063   1.0000
  15.250   1.4280   0.05531   0.04983  -0.0285   0.0062   1.0000
  15.500   1.4220   0.05920   0.05385  -0.0290   0.0061   1.0000
  15.750   1.4159   0.06329   0.05807  -0.0298   0.0060   1.0000
  16.000   1.4082   0.06781   0.06272  -0.0309   0.0059   1.0000
  16.250   1.3991   0.07276   0.06781  -0.0325   0.0058   1.0000
  16.500   1.3901   0.07789   0.07307  -0.0343   0.0057   1.0000
  16.750   1.3782   0.08372   0.07905  -0.0366   0.0056   1.0000
  17.000   1.3653   0.08996   0.08543  -0.0392   0.0057   1.0000
  17.250   1.3529   0.09627   0.09188  -0.0421   0.0056   1.0000
  17.500   1.3391   0.10302   0.09876  -0.0453   0.0056   1.0000
  17.750   1.3257   0.10985   0.10573  -0.0487   0.0056   1.0000
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