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HT05 (ht05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HT05 (ht05-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.49 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht05-il-1000000-n5.txt
Download as CSV file: xf-ht05-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT05                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7797   0.15220   0.15055   0.0551   1.0000   0.0039
 -12.250  -0.7793   0.14704   0.14539   0.0532   1.0000   0.0039
 -11.250  -1.1296   0.03518   0.03282  -0.0115   1.0000   0.0039
 -11.000  -1.1210   0.03137   0.02868  -0.0115   1.0000   0.0040
 -10.750  -1.1074   0.02857   0.02560  -0.0111   1.0000   0.0041
 -10.500  -1.0912   0.02625   0.02298  -0.0106   1.0000   0.0043
 -10.250  -1.0729   0.02429   0.02077  -0.0101   1.0000   0.0044
 -10.000  -1.0531   0.02261   0.01886  -0.0095   1.0000   0.0045
  -9.750  -1.0320   0.02118   0.01722  -0.0090   1.0000   0.0046
  -9.500  -1.0100   0.01990   0.01574  -0.0085   1.0000   0.0048
  -9.250  -0.9871   0.01880   0.01445  -0.0080   1.0000   0.0049
  -9.000  -0.9635   0.01786   0.01336  -0.0076   1.0000   0.0050
  -8.750  -0.9394   0.01699   0.01234  -0.0072   1.0000   0.0050
  -8.500  -0.9166   0.01562   0.01073  -0.0066   1.0000   0.0053
  -8.250  -0.8921   0.01475   0.00974  -0.0062   1.0000   0.0057
  -8.000  -0.8667   0.01415   0.00907  -0.0059   1.0000   0.0060
  -7.750  -0.8410   0.01365   0.00850  -0.0056   1.0000   0.0063
  -7.500  -0.8150   0.01321   0.00801  -0.0053   1.0000   0.0067
  -7.250  -0.7889   0.01277   0.00749  -0.0051   1.0000   0.0072
  -7.000  -0.7628   0.01231   0.00694  -0.0048   1.0000   0.0075
  -6.750  -0.7365   0.01187   0.00642  -0.0045   1.0000   0.0078
  -6.500  -0.7103   0.01139   0.00587  -0.0042   1.0000   0.0080
  -6.250  -0.6843   0.01078   0.00517  -0.0038   1.0000   0.0089
  -6.000  -0.6577   0.01040   0.00477  -0.0036   1.0000   0.0096
  -5.750  -0.6310   0.01008   0.00441  -0.0033   1.0000   0.0104
  -5.500  -0.6042   0.00978   0.00407  -0.0031   1.0000   0.0111
  -5.250  -0.5773   0.00954   0.00380  -0.0028   1.0000   0.0118
  -5.000  -0.5506   0.00917   0.00340  -0.0025   1.0000   0.0133
  -4.750  -0.5238   0.00888   0.00311  -0.0022   1.0000   0.0149
  -4.500  -0.4970   0.00865   0.00285  -0.0020   1.0000   0.0165
  -4.250  -0.4701   0.00845   0.00263  -0.0017   1.0000   0.0176
  -4.000  -0.4434   0.00819   0.00238  -0.0014   1.0000   0.0216
  -3.750  -0.4166   0.00799   0.00220  -0.0010   0.9999   0.0250
  -3.500  -0.3856   0.00777   0.00199  -0.0017   0.9951   0.0306
  -3.250  -0.3551   0.00758   0.00182  -0.0022   0.9886   0.0362
  -3.000  -0.3237   0.00737   0.00166  -0.0030   0.9780   0.0473
  -2.750  -0.2944   0.00729   0.00152  -0.0030   0.9103   0.0601
  -2.500  -0.2750   0.00805   0.00142  -0.0010   0.6481   0.0740
  -2.250  -0.2476   0.00795   0.00134  -0.0009   0.6382   0.0949
  -2.000  -0.2200   0.00786   0.00127  -0.0008   0.6331   0.1137
  -1.750  -0.1923   0.00769   0.00120  -0.0007   0.6280   0.1406
  -1.500  -0.1646   0.00755   0.00115  -0.0006   0.6225   0.1666
  -1.250  -0.1368   0.00738   0.00108  -0.0005   0.6152   0.1959
  -1.000  -0.1090   0.00721   0.00102  -0.0004   0.6062   0.2291
  -0.750  -0.0812   0.00705   0.00097  -0.0004   0.5920   0.2615
  -0.500  -0.0536   0.00688   0.00090  -0.0003   0.5653   0.3100
  -0.250  -0.0265   0.00676   0.00083  -0.0001   0.5142   0.3719
   0.000   0.0001   0.00672   0.00081   0.0000   0.4446   0.4460
   0.250   0.0267   0.00677   0.00083   0.0001   0.3700   0.5141
   0.500   0.0538   0.00688   0.00090   0.0003   0.3095   0.5653
   0.750   0.0814   0.00705   0.00097   0.0003   0.2620   0.5923
   1.000   0.1092   0.00721   0.00102   0.0004   0.2293   0.6061
   1.250   0.1370   0.00738   0.00108   0.0005   0.1960   0.6152
   1.500   0.1648   0.00755   0.00115   0.0006   0.1658   0.6227
   1.750   0.1925   0.00769   0.00120   0.0007   0.1409   0.6279
   2.000   0.2202   0.00786   0.00127   0.0008   0.1140   0.6331
   2.250   0.2478   0.00795   0.00134   0.0009   0.0951   0.6382
   2.500   0.2751   0.00805   0.00142   0.0010   0.0735   0.6483
   2.750   0.2945   0.00729   0.00152   0.0030   0.0602   0.9110
   3.000   0.3239   0.00737   0.00166   0.0030   0.0472   0.9780
   3.250   0.3553   0.00758   0.00182   0.0022   0.0361   0.9887
   3.500   0.3859   0.00777   0.00199   0.0017   0.0305   0.9952
   3.750   0.4167   0.00799   0.00220   0.0010   0.0250   1.0000
   4.000   0.4435   0.00819   0.00238   0.0013   0.0216   1.0000
   4.250   0.4702   0.00845   0.00263   0.0017   0.0177   1.0000
   4.500   0.4971   0.00865   0.00285   0.0019   0.0165   1.0000
   4.750   0.5240   0.00889   0.00311   0.0022   0.0149   1.0000
   5.000   0.5508   0.00918   0.00340   0.0025   0.0133   1.0000
   5.250   0.5775   0.00954   0.00380   0.0028   0.0118   1.0000
   5.500   0.6044   0.00978   0.00407   0.0030   0.0111   1.0000
   5.750   0.6312   0.01008   0.00441   0.0033   0.0104   1.0000
   6.000   0.6578   0.01041   0.00478   0.0036   0.0096   1.0000
   6.250   0.6844   0.01078   0.00518   0.0038   0.0089   1.0000
   6.500   0.7104   0.01143   0.00592   0.0042   0.0080   1.0000
   6.750   0.7367   0.01187   0.00643   0.0045   0.0078   1.0000
   7.000   0.7629   0.01231   0.00695   0.0048   0.0075   1.0000
   7.250   0.7891   0.01276   0.00748   0.0051   0.0072   1.0000
   7.500   0.8151   0.01320   0.00799   0.0053   0.0067   1.0000
   7.750   0.8411   0.01365   0.00849   0.0056   0.0063   1.0000
   8.000   0.8668   0.01415   0.00906   0.0059   0.0060   1.0000
   8.250   0.8922   0.01476   0.00975   0.0062   0.0057   1.0000
   8.500   0.9166   0.01566   0.01078   0.0066   0.0053   1.0000
   8.750   0.9396   0.01698   0.01233   0.0072   0.0051   1.0000
   9.000   0.9637   0.01783   0.01333   0.0076   0.0050   1.0000
   9.250   0.9873   0.01880   0.01446   0.0080   0.0049   1.0000
   9.500   1.0101   0.01991   0.01575   0.0085   0.0048   1.0000
   9.750   1.0322   0.02117   0.01720   0.0090   0.0046   1.0000
  10.000   1.0533   0.02261   0.01885   0.0095   0.0045   1.0000
  10.250   1.0731   0.02429   0.02077   0.0101   0.0044   1.0000
  10.500   1.0915   0.02621   0.02294   0.0106   0.0043   1.0000
  10.750   1.1080   0.02848   0.02549   0.0111   0.0041   1.0000
  11.000   1.1218   0.03122   0.02852   0.0114   0.0040   1.0000
  11.250   1.1311   0.03488   0.03250   0.0115   0.0039   1.0000
  11.500   1.1240   0.04259   0.04070   0.0098   0.0039   1.0000
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