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HT12 (ht12-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HT12 (ht12-il)
Reynolds number: 500,000
Max Cl/Cd: 50.15 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht12-il-500000-n5.txt
Download as CSV file: xf-ht12-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7986   0.11408   0.11187   0.0513   1.0000   0.0068
 -10.000  -0.8039   0.10787   0.10568   0.0484   1.0000   0.0069
  -9.000  -0.9351   0.03589   0.03285  -0.0035   1.0000   0.0064
  -8.750  -0.9263   0.02909   0.02530  -0.0048   1.0000   0.0067
  -8.500  -0.9082   0.02554   0.02125  -0.0050   1.0000   0.0069
  -8.250  -0.8861   0.02349   0.01882  -0.0049   1.0000   0.0073
  -8.000  -0.8633   0.02157   0.01656  -0.0047   1.0000   0.0076
  -7.750  -0.8404   0.01960   0.01431  -0.0046   1.0000   0.0081
  -7.500  -0.8154   0.01850   0.01305  -0.0045   1.0000   0.0084
  -7.250  -0.7900   0.01751   0.01191  -0.0043   1.0000   0.0088
  -7.000  -0.7643   0.01655   0.01079  -0.0041   1.0000   0.0093
  -6.750  -0.7383   0.01563   0.00969  -0.0039   1.0000   0.0099
  -6.500  -0.7121   0.01478   0.00869  -0.0037   1.0000   0.0104
  -6.250  -0.6855   0.01407   0.00784  -0.0035   1.0000   0.0109
  -6.000  -0.6592   0.01316   0.00683  -0.0033   1.0000   0.0119
  -5.750  -0.6323   0.01265   0.00629  -0.0032   1.0000   0.0130
  -5.500  -0.6052   0.01218   0.00573  -0.0031   1.0000   0.0141
  -5.250  -0.5780   0.01167   0.00514  -0.0029   1.0000   0.0152
  -5.000  -0.5506   0.01125   0.00465  -0.0028   1.0000   0.0161
  -4.750  -0.5233   0.01065   0.00401  -0.0026   1.0000   0.0185
  -4.500  -0.4957   0.01033   0.00365  -0.0026   1.0000   0.0212
  -4.250  -0.4680   0.01002   0.00329  -0.0024   1.0000   0.0234
  -4.000  -0.4404   0.00961   0.00289  -0.0023   1.0000   0.0282
  -3.750  -0.4126   0.00935   0.00261  -0.0022   1.0000   0.0329
  -3.500  -0.3848   0.00904   0.00234  -0.0022   1.0000   0.0423
  -3.250  -0.3570   0.00876   0.00209  -0.0021   1.0000   0.0539
  -3.000  -0.3293   0.00848   0.00188  -0.0020   1.0000   0.0714
  -2.750  -0.3015   0.00820   0.00170  -0.0020   1.0000   0.0941
  -2.500  -0.2737   0.00791   0.00153  -0.0020   1.0000   0.1237
  -2.250  -0.2459   0.00761   0.00138  -0.0020   1.0000   0.1616
  -2.000  -0.2181   0.00732   0.00126  -0.0020   1.0000   0.2051
  -1.750  -0.1903   0.00707   0.00117  -0.0019   1.0000   0.2477
  -1.500  -0.1625   0.00684   0.00110  -0.0019   1.0000   0.2898
  -1.250  -0.1346   0.00663   0.00104  -0.0019   1.0000   0.3307
  -1.000  -0.1068   0.00642   0.00099  -0.0018   1.0000   0.3728
  -0.750  -0.0790   0.00620   0.00096  -0.0018   1.0000   0.4193
  -0.500  -0.0464   0.00596   0.00096  -0.0028   0.9608   0.4816
  -0.250  -0.0218   0.00596   0.00096  -0.0015   0.8276   0.5625
   0.000   0.0001   0.00601   0.00094   0.0000   0.6855   0.6873
   0.250   0.0219   0.00595   0.00096   0.0015   0.5630   0.8286
   0.500   0.0466   0.00596   0.00096   0.0028   0.4819   0.9606
   0.750   0.0792   0.00620   0.00096   0.0018   0.4187   1.0000
   1.000   0.1070   0.00642   0.00099   0.0018   0.3722   1.0000
   1.250   0.1348   0.00663   0.00104   0.0019   0.3304   1.0000
   1.500   0.1626   0.00684   0.00110   0.0019   0.2895   1.0000
   2.000   0.2183   0.00733   0.00126   0.0020   0.2043   1.0000
   2.250   0.2461   0.00761   0.00138   0.0020   0.1612   1.0000
   2.500   0.2738   0.00790   0.00153   0.0020   0.1241   1.0000
   2.750   0.3016   0.00820   0.00170   0.0020   0.0940   1.0000
   3.000   0.3294   0.00848   0.00188   0.0020   0.0714   1.0000
   3.250   0.3572   0.00876   0.00209   0.0021   0.0538   1.0000
   3.500   0.3850   0.00904   0.00234   0.0022   0.0422   1.0000
   3.750   0.4128   0.00935   0.00261   0.0022   0.0328   1.0000
   4.000   0.4406   0.00961   0.00290   0.0023   0.0281   1.0000
   4.250   0.4682   0.01001   0.00329   0.0024   0.0234   1.0000
   4.500   0.4959   0.01033   0.00365   0.0025   0.0212   1.0000
   4.750   0.5235   0.01066   0.00402   0.0026   0.0185   1.0000
   5.000   0.5508   0.01125   0.00466   0.0027   0.0161   1.0000
   5.250   0.5782   0.01168   0.00515   0.0029   0.0152   1.0000
   5.500   0.6054   0.01218   0.00574   0.0030   0.0141   1.0000
   5.750   0.6325   0.01267   0.00630   0.0032   0.0130   1.0000
   6.000   0.6595   0.01315   0.00682   0.0033   0.0118   1.0000
   6.250   0.6858   0.01407   0.00784   0.0034   0.0109   1.0000
   6.500   0.7123   0.01478   0.00869   0.0036   0.0104   1.0000
   6.750   0.7386   0.01564   0.00970   0.0039   0.0098   1.0000
   7.000   0.7646   0.01657   0.01081   0.0041   0.0093   1.0000
   7.250   0.7903   0.01753   0.01194   0.0043   0.0088   1.0000
   7.500   0.8157   0.01853   0.01309   0.0044   0.0084   1.0000
   7.750   0.8407   0.01961   0.01433   0.0046   0.0081   1.0000
   8.000   0.8639   0.02142   0.01640   0.0047   0.0076   1.0000
   8.250   0.8863   0.02355   0.01889   0.0048   0.0073   1.0000
   8.500   0.9084   0.02564   0.02135   0.0049   0.0069   1.0000
   8.750   0.9266   0.02911   0.02533   0.0047   0.0067   1.0000
   9.000   0.9354   0.03593   0.03290   0.0034   0.0064   1.0000
   9.500   0.8225   0.09413   0.09201  -0.0414   0.0070   1.0000
   9.750   0.8120   0.10138   0.09923  -0.0454   0.0070   1.0000
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