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HT23 (ht23-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HT23 (ht23-il)
Reynolds number: 50,000
Max Cl/Cd: 28.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht23-il-50000-n5.txt
Download as CSV file: xf-ht23-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT23                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6475   0.09371   0.08705   0.0129   1.0000   0.0540
  -7.750  -0.6373   0.09013   0.08345   0.0143   1.0000   0.0513
  -7.500  -0.6308   0.08527   0.07860   0.0113   1.0000   0.0497
  -7.250  -0.6239   0.07983   0.07314   0.0070   1.0000   0.0481
  -7.000  -0.6157   0.07383   0.06708   0.0022   1.0000   0.0464
  -6.750  -0.6060   0.06705   0.06012  -0.0031   1.0000   0.0444
  -6.500  -0.5929   0.05883   0.05118  -0.0095   1.0000   0.0417
  -6.250  -0.5772   0.05415   0.04624  -0.0109   1.0000   0.0415
  -6.000  -0.5595   0.04948   0.04119  -0.0124   1.0000   0.0419
  -5.750  -0.5412   0.04628   0.03794  -0.0129   1.0000   0.0438
  -5.500  -0.5200   0.04287   0.03418  -0.0136   1.0000   0.0455
  -5.250  -0.4967   0.03920   0.03002  -0.0141   1.0000   0.0464
  -5.000  -0.4719   0.03571   0.02600  -0.0143   1.0000   0.0469
  -4.750  -0.4458   0.03265   0.02242  -0.0143   1.0000   0.0479
  -4.500  -0.4189   0.03008   0.01934  -0.0140   1.0000   0.0503
  -4.250  -0.3915   0.02788   0.01668  -0.0135   1.0000   0.0542
  -4.000  -0.3654   0.02600   0.01467  -0.0131   1.0000   0.0583
  -3.750  -0.3383   0.02432   0.01274  -0.0124   1.0000   0.0634
  -3.500  -0.3119   0.02285   0.01123  -0.0118   1.0000   0.0721
  -3.250  -0.2848   0.02149   0.00974  -0.0112   1.0000   0.0832
  -3.000  -0.2580   0.02025   0.00846  -0.0108   1.0000   0.1037
  -2.750  -0.2314   0.01885   0.00732  -0.0105   1.0000   0.1507
  -2.500  -0.2074   0.01695   0.00647  -0.0104   1.0000   0.3207
  -2.250  -0.1924   0.01513   0.00618  -0.0070   1.0000   0.6263
  -2.000  -0.1357   0.01413   0.00558  -0.0098   1.0000   1.0000
  -1.750  -0.1104   0.01403   0.00514  -0.0094   1.0000   1.0000
  -1.500  -0.0850   0.01396   0.00478  -0.0090   1.0000   1.0000
  -1.250  -0.0595   0.01390   0.00449  -0.0087   1.0000   1.0000
  -1.000  -0.0339   0.01386   0.00425  -0.0083   1.0000   1.0000
  -0.750  -0.0083   0.01384   0.00407  -0.0080   1.0000   1.0000
  -0.500   0.0173   0.01383   0.00396  -0.0076   1.0000   1.0000
  -0.250   0.0429   0.01384   0.00388  -0.0073   1.0000   1.0000
   0.000   0.0684   0.01387   0.00386  -0.0070   1.0000   1.0000
   0.250   0.0937   0.01392   0.00390  -0.0068   1.0000   1.0000
   0.500   0.1187   0.01399   0.00401  -0.0066   1.0000   1.0000
   0.750   0.1542   0.01414   0.00420  -0.0085   0.9678   1.0000
   1.000   0.2053   0.01439   0.00439  -0.0128   0.8699   1.0000
   1.250   0.2403   0.01473   0.00450  -0.0131   0.7811   1.0000
   1.500   0.2650   0.01516   0.00463  -0.0114   0.7135   1.0000
   1.750   0.2885   0.01562   0.00479  -0.0098   0.6610   1.0000
   2.000   0.3128   0.01608   0.00501  -0.0086   0.6174   1.0000
   2.250   0.3377   0.01654   0.00528  -0.0076   0.5794   1.0000
   2.500   0.3631   0.01700   0.00561  -0.0068   0.5463   1.0000
   2.750   0.3888   0.01745   0.00594  -0.0061   0.5158   1.0000
   3.000   0.4147   0.01791   0.00631  -0.0055   0.4870   1.0000
   3.250   0.4409   0.01837   0.00673  -0.0050   0.4595   1.0000
   3.500   0.4672   0.01884   0.00721  -0.0045   0.4332   1.0000
   3.750   0.4934   0.01933   0.00769  -0.0041   0.4079   1.0000
   4.000   0.5193   0.01983   0.00816  -0.0036   0.3836   1.0000
   4.250   0.5454   0.02034   0.00872  -0.0032   0.3581   1.0000
   4.500   0.5715   0.02088   0.00935  -0.0028   0.3328   1.0000
   4.750   0.5974   0.02144   0.00993  -0.0024   0.3076   1.0000
   5.000   0.6229   0.02201   0.01051  -0.0019   0.2818   1.0000
   5.250   0.6482   0.02262   0.01116  -0.0015   0.2543   1.0000
   5.500   0.6733   0.02329   0.01191  -0.0012   0.2260   1.0000
   5.750   0.6980   0.02408   0.01272  -0.0009   0.1979   1.0000
   6.000   0.7225   0.02501   0.01369  -0.0006   0.1708   1.0000
   6.250   0.7466   0.02615   0.01488  -0.0003   0.1466   1.0000
   6.500   0.7699   0.02740   0.01610   0.0001   0.1278   1.0000
   6.750   0.7933   0.02891   0.01774   0.0005   0.1129   1.0000
   7.000   0.8161   0.03049   0.01941   0.0009   0.1016   1.0000
   7.250   0.8389   0.03221   0.02140   0.0013   0.0910   1.0000
   7.500   0.8610   0.03437   0.02383   0.0018   0.0849   1.0000
   7.750   0.8823   0.03654   0.02631   0.0022   0.0788   1.0000
   8.000   0.9022   0.03882   0.02880   0.0025   0.0734   1.0000
   8.250   0.9202   0.04199   0.03251   0.0027   0.0693   1.0000
   8.500   0.9365   0.04520   0.03611   0.0029   0.0665   1.0000
   8.750   0.9527   0.04785   0.03890   0.0031   0.0637   1.0000
   9.000   0.9584   0.05281   0.04452   0.0023   0.0614   1.0000
   9.250   0.9564   0.05856   0.05087   0.0006   0.0597   1.0000
   9.500   0.9466   0.06502   0.05775  -0.0022   0.0589   1.0000
   9.750   0.9269   0.07265   0.06562  -0.0071   0.0591   1.0000
  10.000   0.9006   0.08225   0.07529  -0.0158   0.0603   1.0000
  10.250   0.8796   0.09265   0.08566  -0.0240   0.0611   1.0000
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