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HT12 (ht12-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HT12 (ht12-il)
Reynolds number: 100,000
Max Cl/Cd: 26.77 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht12-il-100000.txt
Download as CSV file: xf-ht12-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT12                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.7389   0.11856   0.11372   0.0468   1.0000   0.0914
  -9.000  -0.7485   0.11495   0.11019   0.0405   1.0000   0.0941
  -8.750  -0.7616   0.11105   0.10642   0.0319   1.0000   0.0948
  -8.500  -0.7336   0.10627   0.10152   0.0419   1.0000   0.1014
  -8.250  -0.7363   0.10233   0.09764   0.0380   1.0000   0.1061
  -8.000  -0.7490   0.09696   0.09233   0.0231   1.0000   0.1082
  -7.750  -0.7354   0.09300   0.08840   0.0316   1.0000   0.1118
  -7.500  -0.6245   0.07852   0.07414   0.0231   1.0000   0.1269
  -7.250  -0.6279   0.07406   0.06972   0.0207   1.0000   0.1319
  -7.000  -0.7138   0.07858   0.07396   0.0202   1.0000   0.1268
  -6.750  -0.7054   0.07199   0.06721   0.0098   1.0000   0.1372
  -6.500  -0.6907   0.06882   0.06409   0.0129   1.0000   0.1415
  -6.250  -0.6767   0.06342   0.05854   0.0077   1.0000   0.1527
  -6.000  -0.6502   0.04679   0.04069  -0.0057   1.0000   0.0965
  -5.750  -0.6237   0.03646   0.02912  -0.0074   1.0000   0.0672
  -5.500  -0.5982   0.03311   0.02501  -0.0074   1.0000   0.0685
  -5.250  -0.5724   0.02935   0.02067  -0.0073   1.0000   0.0685
  -5.000  -0.5464   0.02547   0.01639  -0.0072   1.0000   0.0698
  -4.750  -0.5200   0.02337   0.01413  -0.0069   1.0000   0.0752
  -4.500  -0.4917   0.02166   0.01196  -0.0064   1.0000   0.0820
  -4.250  -0.4649   0.01960   0.00991  -0.0060   1.0000   0.0896
  -4.000  -0.4379   0.01820   0.00848  -0.0056   1.0000   0.1043
  -3.750  -0.4109   0.01671   0.00700  -0.0050   1.0000   0.1232
  -3.500  -0.3847   0.01541   0.00592  -0.0046   1.0000   0.1609
  -3.250  -0.3590   0.01403   0.00506  -0.0043   1.0000   0.2385
  -3.000  -0.3339   0.01294   0.00455  -0.0038   1.0000   0.3568
  -2.750  -0.3093   0.01209   0.00417  -0.0030   1.0000   0.4647
  -2.500  -0.2869   0.01115   0.00384  -0.0014   1.0000   0.5908
  -2.250  -0.2699   0.01009   0.00366   0.0029   1.0000   0.8276
  -2.000  -0.2140   0.00977   0.00320  -0.0019   1.0000   1.0000
  -1.750  -0.1873   0.00969   0.00289  -0.0018   1.0000   1.0000
  -1.500  -0.1606   0.00963   0.00262  -0.0016   1.0000   1.0000
  -1.250  -0.1339   0.00958   0.00243  -0.0013   1.0000   1.0000
  -1.000  -0.1072   0.00954   0.00227  -0.0011   1.0000   1.0000
  -0.750  -0.0804   0.00951   0.00216  -0.0008   1.0000   1.0000
  -0.500  -0.0536   0.00949   0.00208  -0.0005   1.0000   1.0000
  -0.250  -0.0268   0.00948   0.00202  -0.0003   1.0000   1.0000
   0.000   0.0001   0.00948   0.00201   0.0000   1.0000   1.0000
   0.250   0.0269   0.00948   0.00202   0.0003   1.0000   1.0000
   0.500   0.0538   0.00949   0.00208   0.0005   1.0000   1.0000
   0.750   0.0806   0.00951   0.00216   0.0008   1.0000   1.0000
   1.000   0.1073   0.00954   0.00227   0.0011   1.0000   1.0000
   1.250   0.1341   0.00958   0.00243   0.0013   1.0000   1.0000
   1.500   0.1608   0.00963   0.00262   0.0016   1.0000   1.0000
   1.750   0.1875   0.00969   0.00289   0.0018   1.0000   1.0000
   2.000   0.2142   0.00977   0.00320   0.0019   1.0000   1.0000
   2.250   0.2701   0.01009   0.00366  -0.0029   0.8251   1.0000
   2.500   0.2870   0.01116   0.00384   0.0014   0.5899   1.0000
   2.750   0.3095   0.01210   0.00418   0.0030   0.4641   1.0000
   3.000   0.3340   0.01295   0.00456   0.0038   0.3560   1.0000
   3.250   0.3591   0.01404   0.00506   0.0043   0.2379   1.0000
   3.500   0.3849   0.01542   0.00593   0.0046   0.1606   1.0000
   3.750   0.4110   0.01672   0.00701   0.0050   0.1231   1.0000
   4.000   0.4381   0.01821   0.00849   0.0056   0.1043   1.0000
   4.250   0.4651   0.01960   0.00992   0.0060   0.0895   1.0000
   4.500   0.4919   0.02167   0.01197   0.0064   0.0819   1.0000
   4.750   0.5202   0.02339   0.01415   0.0069   0.0751   1.0000
   5.000   0.5466   0.02548   0.01641   0.0071   0.0697   1.0000
   5.250   0.5726   0.02937   0.02072   0.0072   0.0684   1.0000
   5.500   0.5985   0.03303   0.02493   0.0074   0.0685   1.0000
   5.750   0.6238   0.03652   0.02917   0.0073   0.0672   1.0000
   6.000   0.6491   0.04725   0.04127   0.0050   0.0928   1.0000
   6.250   0.6769   0.06344   0.05856  -0.0077   0.1525   1.0000
   6.500   0.6910   0.06885   0.06413  -0.0129   0.1413   1.0000
   6.750   0.7057   0.07203   0.06724  -0.0098   0.1371   1.0000
   7.000   0.7142   0.07862   0.07400  -0.0203   0.1267   1.0000
   7.250   0.7279   0.08162   0.07696  -0.0153   0.1232   1.0000
   7.500   0.7275   0.08910   0.08451  -0.0303   0.1166   1.0000
   7.750   0.7358   0.09305   0.08845  -0.0317   0.1117   1.0000
   8.000   0.7495   0.09701   0.09238  -0.0230   0.1081   1.0000
   8.250   0.7368   0.10240   0.09771  -0.0381   0.1060   1.0000
   8.500   0.7341   0.10634   0.10160  -0.0420   0.1014   1.0000
   8.750   0.7621   0.11112   0.10648  -0.0320   0.0947   1.0000
   9.000   0.7494   0.11504   0.11028  -0.0406   0.0941   1.0000
   9.250   0.7397   0.11864   0.11380  -0.0469   0.0914   1.0000
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