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HT22 (ht22-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HT22 (ht22-il)
Reynolds number: 50,000
Max Cl/Cd: 25.34 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht22-il-50000.txt
Download as CSV file: xf-ht22-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT22                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6710   0.11894   0.11231   0.0379   1.0001   0.1743
  -8.250  -0.6515   0.11303   0.10638   0.0405   1.0001   0.1846
  -8.000  -0.6685   0.11204   0.10554   0.0343   1.0001   0.1890
  -7.750  -0.6485   0.10630   0.09978   0.0375   1.0001   0.2011
  -7.500  -0.6407   0.10206   0.09559   0.0375   1.0001   0.2097
  -7.250  -0.6472   0.09936   0.09300   0.0323   1.0001   0.2190
  -7.000  -0.6445   0.09628   0.08995   0.0280   1.0001   0.2324
  -6.750  -0.6358   0.09216   0.08588   0.0276   1.0001   0.2470
  -6.500  -0.6227   0.08756   0.08131   0.0304   1.0001   0.2631
  -6.250  -0.6101   0.08362   0.07738   0.0325   1.0001   0.2820
  -5.500  -0.5843   0.07357   0.06749   0.0363   1.0001   0.3741
  -5.000  -0.5640   0.06723   0.06128   0.0469   1.0001   0.4677
  -4.250  -0.4260   0.04321   0.03538  -0.0121   1.0001   0.1933
  -4.000  -0.3832   0.03738   0.02842  -0.0159   1.0001   0.1430
  -3.750  -0.3530   0.03372   0.02426  -0.0166   1.0001   0.1366
  -3.500  -0.3218   0.03068   0.02053  -0.0169   1.0001   0.1340
  -3.250  -0.2901   0.02823   0.01737  -0.0166   1.0001   0.1316
  -3.000  -0.2623   0.02569   0.01477  -0.0163   1.0001   0.1373
  -2.750  -0.2324   0.02385   0.01250  -0.0157   1.0001   0.1466
  -2.500  -0.2037   0.02195   0.01052  -0.0150   1.0001   0.1585
  -2.250  -0.1759   0.02026   0.00888  -0.0141   1.0001   0.1817
  -2.000  -0.1476   0.01859   0.00736  -0.0133   1.0001   0.2235
  -1.750  -0.1117   0.01368   0.00536  -0.0116   1.0001   0.9999
  -1.500  -0.0847   0.01362   0.00469  -0.0110   1.0001   0.9999
  -1.250  -0.0583   0.01356   0.00426  -0.0105   1.0001   0.9999
  -1.000  -0.0320   0.01353   0.00392  -0.0101   1.0001   0.9999
  -0.750  -0.0057   0.01350   0.00368  -0.0098   1.0001   0.9999
  -0.500   0.0205   0.01349   0.00351  -0.0094   1.0001   0.9999
  -0.250   0.0467   0.01349   0.00337  -0.0091   1.0001   0.9999
   0.000   0.0728   0.01351   0.00330  -0.0087   1.0001   0.9999
   0.250   0.0988   0.01353   0.00328  -0.0084   1.0001   0.9999
   0.500   0.1248   0.01357   0.00332  -0.0081   1.0001   0.9999
   0.750   0.1505   0.01363   0.00340  -0.0078   1.0001   0.9999
   1.000   0.1761   0.01371   0.00354  -0.0075   1.0001   0.9999
   1.250   0.2015   0.01381   0.00374  -0.0073   1.0001   0.9999
   1.500   0.2264   0.01394   0.00403  -0.0072   1.0001   0.9999
   1.750   0.2505   0.01414   0.00445  -0.0072   1.0001   0.9999
   2.000   0.2719   0.01455   0.00512  -0.0079   1.0001   0.9999
   2.250   0.3706   0.01530   0.00631  -0.0232   0.8911   0.9999
   2.500   0.4029   0.01590   0.00669  -0.0209   0.7807   0.9999
   2.750   0.4206   0.01667   0.00712  -0.0168   0.7030   0.9999
   3.000   0.4403   0.01749   0.00762  -0.0135   0.6373   0.9999
   3.250   0.4620   0.01836   0.00825  -0.0112   0.5742   0.9999
   3.500   0.4843   0.01926   0.00891  -0.0091   0.5139   0.9999
   3.750   0.5068   0.02022   0.00968  -0.0072   0.4544   0.9999
   4.000   0.5300   0.02126   0.01048  -0.0056   0.3952   0.9999
   4.250   0.5538   0.02238   0.01137  -0.0042   0.3378   0.9999
   4.500   0.5783   0.02366   0.01247  -0.0031   0.2883   0.9999
   4.750   0.6030   0.02502   0.01365  -0.0021   0.2486   0.9999
   5.000   0.6288   0.02672   0.01543  -0.0015   0.2186   0.9999
   5.250   0.6546   0.02853   0.01736  -0.0010   0.1955   0.9999
   5.500   0.6806   0.03080   0.01981  -0.0005   0.1805   0.9999
   5.750   0.7054   0.03295   0.02211  -0.0001   0.1656   0.9999
   6.000   0.7305   0.03664   0.02660  -0.0004   0.1589   0.9999
   6.250   0.7540   0.04015   0.03054  -0.0005   0.1537   0.9999
   6.500   0.7748   0.04425   0.03512  -0.0011   0.1480   0.9999
   6.750   0.7924   0.04979   0.04135  -0.0028   0.1461   0.9999
   7.000   0.8077   0.05592   0.04792  -0.0049   0.1486   0.9999
   7.250   0.8123   0.06638   0.05905  -0.0123   0.1612   0.9999
   7.500   0.8192   0.07797   0.07090  -0.0200   0.1925   0.9999
   7.750   0.7648   0.09872   0.09164  -0.0589   0.3300   0.9999
   8.000   0.7838   0.10366   0.09665  -0.0578   0.3209   0.9999
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