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HT12 (ht12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HT12 (ht12-il)
Reynolds number: 1,000,000
Max Cl/Cd: 64.68 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht12-il-1000000-n5.txt
Download as CSV file: xf-ht12-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -1.1394   0.04050   0.03852  -0.0022   1.0000   0.0039
 -11.000  -1.1384   0.03403   0.03160  -0.0045   1.0000   0.0040
 -10.750  -1.1266   0.03027   0.02749  -0.0051   1.0000   0.0041
 -10.500  -1.1104   0.02748   0.02438  -0.0053   1.0000   0.0042
 -10.250  -1.0917   0.02520   0.02183  -0.0052   1.0000   0.0043
 -10.000  -1.0711   0.02333   0.01970  -0.0051   1.0000   0.0044
  -9.750  -1.0493   0.02174   0.01787  -0.0050   1.0000   0.0045
  -9.500  -1.0263   0.02039   0.01631  -0.0048   1.0000   0.0046
  -9.250  -1.0026   0.01920   0.01494  -0.0046   1.0000   0.0047
  -9.000  -0.9783   0.01818   0.01375  -0.0044   1.0000   0.0048
  -8.750  -0.9547   0.01671   0.01205  -0.0041   1.0000   0.0050
  -8.500  -0.9300   0.01560   0.01077  -0.0040   1.0000   0.0053
  -8.250  -0.9043   0.01487   0.00995  -0.0038   1.0000   0.0055
  -8.000  -0.8782   0.01428   0.00926  -0.0036   1.0000   0.0058
  -7.750  -0.8518   0.01377   0.00868  -0.0035   1.0000   0.0062
  -7.500  -0.8253   0.01327   0.00812  -0.0033   1.0000   0.0065
  -7.250  -0.7987   0.01278   0.00754  -0.0032   1.0000   0.0069
  -7.000  -0.7719   0.01228   0.00697  -0.0030   1.0000   0.0072
  -6.750  -0.7450   0.01183   0.00642  -0.0029   1.0000   0.0074
  -6.500  -0.7182   0.01115   0.00564  -0.0028   1.0000   0.0080
  -6.250  -0.6911   0.01068   0.00513  -0.0026   1.0000   0.0086
  -6.000  -0.6638   0.01032   0.00474  -0.0025   1.0000   0.0093
  -5.750  -0.6364   0.00998   0.00436  -0.0024   1.0000   0.0100
  -5.500  -0.6089   0.00967   0.00400  -0.0023   1.0000   0.0106
  -5.250  -0.5813   0.00938   0.00367  -0.0022   1.0000   0.0114
  -5.000  -0.5537   0.00901   0.00329  -0.0021   1.0000   0.0131
  -4.750  -0.5260   0.00874   0.00300  -0.0020   1.0000   0.0144
  -4.500  -0.4982   0.00851   0.00275  -0.0019   1.0000   0.0157
  -4.250  -0.4703   0.00825   0.00247  -0.0019   1.0000   0.0178
  -4.000  -0.4424   0.00801   0.00224  -0.0018   1.0000   0.0212
  -3.750  -0.4145   0.00781   0.00204  -0.0017   1.0000   0.0243
  -3.500  -0.3865   0.00758   0.00185  -0.0017   1.0000   0.0300
  -3.250  -0.3585   0.00739   0.00167  -0.0016   1.0000   0.0366
  -3.000  -0.3305   0.00717   0.00151  -0.0015   1.0000   0.0474
  -2.750  -0.3025   0.00697   0.00137  -0.0015   1.0000   0.0600
  -2.500  -0.2744   0.00676   0.00124  -0.0015   1.0000   0.0781
  -2.250  -0.2464   0.00655   0.00112  -0.0015   1.0000   0.0997
  -2.000  -0.2183   0.00633   0.00101  -0.0014   1.0000   0.1262
  -1.750  -0.1902   0.00611   0.00093  -0.0014   1.0000   0.1595
  -1.500  -0.1580   0.00592   0.00087  -0.0024   0.9501   0.2006
  -1.250  -0.1366   0.00608   0.00083  -0.0005   0.8428   0.2319
  -1.000  -0.1111   0.00628   0.00077   0.0001   0.7316   0.2662
  -0.750  -0.0838   0.00651   0.00073   0.0002   0.6152   0.2999
  -0.500  -0.0560   0.00669   0.00071   0.0001   0.5180   0.3335
  -0.250  -0.0280   0.00675   0.00069   0.0001   0.4613   0.3684
   0.000   0.0001   0.00676   0.00069   0.0000   0.4110   0.4111
   0.250   0.0281   0.00675   0.00069  -0.0001   0.3674   0.4607
   0.500   0.0562   0.00668   0.00071  -0.0002   0.3330   0.5206
   0.750   0.0840   0.00651   0.00073  -0.0002   0.2998   0.6167
   1.000   0.1113   0.00628   0.00077  -0.0002   0.2664   0.7307
   1.250   0.1368   0.00608   0.00083   0.0005   0.2318   0.8427
   1.500   0.1582   0.00592   0.00087   0.0024   0.2005   0.9500
   1.750   0.1904   0.00611   0.00093   0.0014   0.1591   1.0000
   2.000   0.2185   0.00633   0.00101   0.0014   0.1275   1.0000
   2.250   0.2466   0.00655   0.00112   0.0015   0.0996   1.0000
   2.500   0.2746   0.00676   0.00124   0.0015   0.0783   1.0000
   2.750   0.3027   0.00697   0.00137   0.0015   0.0601   1.0000
   3.000   0.3307   0.00718   0.00152   0.0015   0.0471   1.0000
   3.250   0.3587   0.00739   0.00167   0.0016   0.0366   1.0000
   3.500   0.3867   0.00758   0.00185   0.0016   0.0299   1.0000
   3.750   0.4147   0.00781   0.00204   0.0017   0.0243   1.0000
   4.000   0.4426   0.00801   0.00225   0.0018   0.0213   1.0000
   4.250   0.4705   0.00825   0.00247   0.0018   0.0178   1.0000
   4.500   0.4984   0.00851   0.00275   0.0019   0.0157   1.0000
   4.750   0.5262   0.00875   0.00301   0.0020   0.0144   1.0000
   5.000   0.5539   0.00902   0.00329   0.0021   0.0130   1.0000
   5.250   0.5815   0.00939   0.00368   0.0022   0.0113   1.0000
   5.500   0.6091   0.00968   0.00400   0.0023   0.0106   1.0000
   5.750   0.6366   0.00999   0.00436   0.0024   0.0099   1.0000
   6.000   0.6641   0.01032   0.00474   0.0025   0.0093   1.0000
   6.250   0.6914   0.01069   0.00513   0.0026   0.0086   1.0000
   6.500   0.7185   0.01115   0.00564   0.0027   0.0080   1.0000
   6.750   0.7452   0.01184   0.00643   0.0029   0.0074   1.0000
   7.000   0.7722   0.01229   0.00697   0.0030   0.0072   1.0000
   7.250   0.7989   0.01280   0.00757   0.0032   0.0069   1.0000
   7.500   0.8256   0.01329   0.00814   0.0033   0.0066   1.0000
   7.750   0.8522   0.01376   0.00867   0.0035   0.0061   1.0000
   8.000   0.8785   0.01430   0.00929   0.0036   0.0058   1.0000
   8.250   0.9046   0.01489   0.00997   0.0038   0.0056   1.0000
   8.500   0.9303   0.01561   0.01079   0.0039   0.0053   1.0000
   8.750   0.9551   0.01668   0.01202   0.0041   0.0050   1.0000
   9.000   0.9786   0.01818   0.01375   0.0043   0.0048   1.0000
   9.250   1.0030   0.01919   0.01493   0.0045   0.0047   1.0000
   9.500   1.0267   0.02038   0.01630   0.0047   0.0046   1.0000
   9.750   1.0496   0.02174   0.01787   0.0049   0.0045   1.0000
  10.000   1.0715   0.02332   0.01970   0.0051   0.0044   1.0000
  10.250   1.0921   0.02520   0.02182   0.0052   0.0043   1.0000
  10.500   1.1108   0.02749   0.02439   0.0052   0.0042   1.0000
  10.750   1.1269   0.03032   0.02754   0.0050   0.0041   1.0000
  11.000   1.1386   0.03412   0.03170   0.0044   0.0040   1.0000
  11.250   1.1394   0.04065   0.03868   0.0021   0.0039   1.0000
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