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HT05 (ht05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HT05 (ht05-il)
Reynolds number: 1,000,000
Max Cl/Cd: 57.72 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht05-il-1000000.txt
Download as CSV file: xf-ht05-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7480   0.13263   0.13101   0.0465   1.0000   0.0106
 -10.750  -0.7462   0.12745   0.12584   0.0439   1.0000   0.0114
  -8.750  -0.8935   0.03272   0.03017  -0.0099   1.0000   0.0074
  -8.500  -0.8821   0.02810   0.02506  -0.0096   1.0000   0.0076
  -8.250  -0.8639   0.02548   0.02211  -0.0091   1.0000   0.0078
  -8.000  -0.8416   0.02411   0.02053  -0.0087   1.0000   0.0079
  -7.750  -0.8289   0.01885   0.01455  -0.0075   1.0000   0.0082
  -7.500  -0.8084   0.01630   0.01165  -0.0066   1.0000   0.0086
  -7.250  -0.7839   0.01532   0.01055  -0.0062   1.0000   0.0091
  -7.000  -0.7582   0.01476   0.00991  -0.0059   1.0000   0.0096
  -6.750  -0.7322   0.01431   0.00939  -0.0056   1.0000   0.0103
  -6.500  -0.7063   0.01368   0.00867  -0.0052   1.0000   0.0111
  -6.250  -0.6803   0.01306   0.00795  -0.0049   1.0000   0.0116
  -6.000  -0.6538   0.01264   0.00746  -0.0045   1.0000   0.0119
  -5.750  -0.6299   0.01099   0.00557  -0.0038   1.0000   0.0131
  -5.500  -0.6036   0.01045   0.00499  -0.0035   1.0000   0.0143
  -5.250  -0.5769   0.01010   0.00461  -0.0032   1.0000   0.0155
  -5.000  -0.5501   0.00983   0.00431  -0.0029   1.0000   0.0169
  -4.750  -0.5231   0.00963   0.00409  -0.0026   1.0000   0.0176
  -4.500  -0.4971   0.00883   0.00317  -0.0021   1.0000   0.0211
  -4.250  -0.4703   0.00856   0.00289  -0.0018   1.0000   0.0238
  -4.000  -0.4434   0.00838   0.00271  -0.0015   1.0000   0.0256
  -3.750  -0.4169   0.00797   0.00230  -0.0011   1.0000   0.0336
  -3.500  -0.3903   0.00770   0.00204  -0.0007   1.0000   0.0422
  -3.250  -0.3639   0.00744   0.00185  -0.0004   1.0000   0.0552
  -3.000  -0.3376   0.00721   0.00169   0.0000   1.0000   0.0733
  -2.750  -0.3115   0.00695   0.00155   0.0005   1.0000   0.0991
  -2.500  -0.2855   0.00673   0.00143   0.0009   1.0000   0.1267
  -2.250  -0.2596   0.00651   0.00133   0.0014   1.0000   0.1583
  -2.000  -0.2314   0.00629   0.00124   0.0013   0.9991   0.1907
  -1.750  -0.1950   0.00602   0.00115  -0.0007   0.9943   0.2380
  -1.500  -0.1608   0.00574   0.00106  -0.0021   0.9837   0.2937
  -1.250  -0.1277   0.00540   0.00099  -0.0033   0.9628   0.3746
  -1.000  -0.1024   0.00513   0.00094  -0.0025   0.9002   0.4761
  -0.750  -0.0831   0.00574   0.00096  -0.0005   0.6630   0.5492
  -0.500  -0.0557   0.00584   0.00106  -0.0003   0.6476   0.5962
  -0.250  -0.0278   0.00598   0.00113  -0.0001   0.6374   0.6155
   0.000   0.0001   0.00606   0.00117   0.0000   0.6276   0.6278
   0.250   0.0280   0.00598   0.00113   0.0001   0.6152   0.6374
   0.500   0.0559   0.00584   0.00106   0.0003   0.5959   0.6476
   0.750   0.0833   0.00574   0.00096   0.0004   0.5496   0.6633
   1.000   0.1026   0.00513   0.00094   0.0025   0.4761   0.8997
   1.250   0.1279   0.00540   0.00099   0.0033   0.3750   0.9626
   1.500   0.1611   0.00575   0.00107   0.0021   0.2925   0.9840
   1.750   0.1952   0.00602   0.00115   0.0007   0.2380   0.9943
   2.000   0.2315   0.00629   0.00124  -0.0013   0.1908   0.9991
   2.250   0.2597   0.00651   0.00133  -0.0014   0.1582   1.0000
   2.500   0.2856   0.00673   0.00144  -0.0009   0.1264   1.0000
   2.750   0.3116   0.00695   0.00155  -0.0005   0.0991   1.0000
   3.000   0.3377   0.00721   0.00169   0.0000   0.0732   1.0000
   3.250   0.3640   0.00745   0.00185   0.0004   0.0552   1.0000
   3.500   0.3905   0.00770   0.00204   0.0007   0.0421   1.0000
   3.750   0.4171   0.00797   0.00230   0.0011   0.0336   1.0000
   4.000   0.4436   0.00838   0.00270   0.0015   0.0257   1.0000
   4.250   0.4705   0.00855   0.00289   0.0018   0.0237   1.0000
   4.500   0.4973   0.00883   0.00318   0.0021   0.0210   1.0000
   4.750   0.5233   0.00961   0.00407   0.0026   0.0177   1.0000
   5.000   0.5503   0.00982   0.00430   0.0029   0.0169   1.0000
   5.250   0.5771   0.01009   0.00459   0.0032   0.0155   1.0000
   5.500   0.6038   0.01046   0.00500   0.0035   0.0143   1.0000
   5.750   0.6300   0.01102   0.00560   0.0038   0.0131   1.0000
   6.000   0.6540   0.01265   0.00747   0.0045   0.0119   1.0000
   6.250   0.6804   0.01306   0.00795   0.0049   0.0116   1.0000
   6.500   0.7064   0.01369   0.00868   0.0052   0.0111   1.0000
   6.750   0.7324   0.01428   0.00936   0.0056   0.0103   1.0000
   7.000   0.7584   0.01474   0.00988   0.0059   0.0096   1.0000
   7.250   0.7840   0.01531   0.01054   0.0062   0.0091   1.0000
   7.500   0.8084   0.01635   0.01170   0.0066   0.0087   1.0000
   7.750   0.8285   0.01904   0.01476   0.0075   0.0082   1.0000
   8.000   0.8426   0.02378   0.02017   0.0086   0.0079   1.0000
   8.250   0.8643   0.02538   0.02200   0.0091   0.0078   1.0000
   8.500   0.8828   0.02791   0.02485   0.0096   0.0076   1.0000
   8.750   0.8941   0.03260   0.03004   0.0099   0.0074   1.0000
  11.500   0.6005   0.12958   0.12804  -0.0291   0.0119   1.0000
  11.750   0.6004   0.13354   0.13200  -0.0302   0.0118   1.0000
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