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HT22 (ht22-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HT22 (ht22-il)
Reynolds number: 100,000
Max Cl/Cd: 34.97 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht22-il-100000.txt
Download as CSV file: xf-ht22-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6506   0.10712   0.10233   0.0347   1.0001   0.0721
  -8.000  -0.6531   0.10395   0.09923   0.0285   1.0001   0.0741
  -7.750  -0.6513   0.10000   0.09529   0.0153   1.0001   0.0750
  -7.500  -0.6448   0.09407   0.08941   0.0154   1.0001   0.0761
  -7.250  -0.6347   0.09037   0.08574   0.0219   1.0001   0.0787
  -7.000  -0.6247   0.08643   0.08181   0.0200   1.0001   0.0821
  -6.750  -0.6119   0.08162   0.07695   0.0117   1.0001   0.0871
  -6.500  -0.5978   0.07553   0.07072   0.0020   1.0001   0.0903
  -6.250  -0.5868   0.07206   0.06734   0.0056   1.0001   0.0935
  -6.000  -0.5624   0.06757   0.06235  -0.0064   1.0001   0.1036
  -5.750  -0.5515   0.06270   0.05777  -0.0029   1.0001   0.1062
  -5.500  -0.5291   0.05862   0.05337  -0.0080   1.0001   0.1185
  -5.000  -0.4938   0.05169   0.04648  -0.0076   1.0001   0.1409
  -4.750  -0.4700   0.04805   0.04253  -0.0109   1.0001   0.1619
  -4.500  -0.4500   0.04466   0.03916  -0.0108   1.0001   0.1777
  -4.250  -0.4287   0.04176   0.03625  -0.0106   1.0001   0.1973
  -4.000  -0.4073   0.03903   0.03346  -0.0106   1.0001   0.2266
  -3.750  -0.3401   0.02781   0.01979  -0.0160   1.0001   0.0774
  -3.500  -0.3097   0.02592   0.01727  -0.0154   1.0001   0.0754
  -3.250  -0.2815   0.02296   0.01400  -0.0150   1.0001   0.0739
  -3.000  -0.2527   0.02085   0.01152  -0.0145   1.0001   0.0743
  -2.750  -0.2254   0.01889   0.00951  -0.0142   1.0001   0.0808
  -2.500  -0.1971   0.01749   0.00794  -0.0135   1.0001   0.0866
  -2.250  -0.1700   0.01608   0.00657  -0.0130   1.0001   0.0972
  -2.000  -0.1433   0.01483   0.00543  -0.0123   1.0001   0.1122
  -1.750  -0.1171   0.01369   0.00447  -0.0117   1.0001   0.1450
  -1.500  -0.0852   0.00962   0.00350  -0.0109   1.0001   0.9999
  -1.250  -0.0584   0.00958   0.00313  -0.0104   1.0001   0.9999
  -1.000  -0.0318   0.00955   0.00286  -0.0100   1.0001   0.9999
  -0.750  -0.0052   0.00953   0.00268  -0.0096   1.0001   0.9999
  -0.500   0.0214   0.00953   0.00254  -0.0093   1.0001   0.9999
  -0.250   0.0479   0.00953   0.00245  -0.0089   1.0001   0.9999
   0.000   0.0744   0.00954   0.00240  -0.0086   1.0001   0.9999
   0.250   0.1007   0.00956   0.00239  -0.0083   1.0001   0.9999
   0.500   0.1270   0.00959   0.00242  -0.0080   1.0001   0.9999
   0.750   0.1532   0.00964   0.00249  -0.0077   1.0001   0.9999
   1.000   0.1793   0.00970   0.00260  -0.0074   1.0001   0.9999
   1.250   0.2051   0.00978   0.00277  -0.0072   1.0001   0.9999
   1.500   0.2307   0.00990   0.00303  -0.0072   1.0001   0.9999
   1.750   0.2957   0.01009   0.00334  -0.0145   0.9000   0.9999
   2.000   0.3242   0.01053   0.00340  -0.0126   0.7598   0.9999
   2.250   0.3453   0.01112   0.00354  -0.0100   0.6662   0.9999
   2.500   0.3685   0.01170   0.00379  -0.0084   0.5969   0.9999
   2.750   0.3931   0.01225   0.00405  -0.0074   0.5402   0.9999
   3.000   0.4182   0.01278   0.00434  -0.0065   0.4903   0.9999
   3.250   0.4436   0.01329   0.00466  -0.0058   0.4424   0.9999
   3.500   0.4691   0.01379   0.00498  -0.0052   0.3951   0.9999
   3.750   0.4947   0.01432   0.00535  -0.0046   0.3461   0.9999
   4.000   0.5203   0.01489   0.00572  -0.0042   0.2935   0.9999
   4.250   0.5459   0.01561   0.00622  -0.0038   0.2390   0.9999
   4.500   0.5712   0.01658   0.00689  -0.0034   0.1932   0.9999
   4.750   0.5970   0.01768   0.00791  -0.0029   0.1592   0.9999
   5.000   0.6223   0.01893   0.00893  -0.0026   0.1368   0.9999
   5.250   0.6485   0.02018   0.01024  -0.0021   0.1207   0.9999
   5.500   0.6743   0.02180   0.01177  -0.0017   0.1100   0.9999
   5.750   0.7008   0.02299   0.01326  -0.0012   0.0999   0.9999
   6.000   0.7266   0.02500   0.01544  -0.0008   0.0939   0.9999
   6.250   0.7526   0.02712   0.01798  -0.0003   0.0896   0.9999
   6.500   0.7774   0.02914   0.02014   0.0000   0.0851   0.9999
   6.750   0.8005   0.03207   0.02357   0.0002   0.0811   0.9999
   7.000   0.8224   0.03575   0.02795   0.0005   0.0799   0.9999
   7.250   0.8414   0.04042   0.03327   0.0004   0.0800   0.9999
   7.500   0.8571   0.04582   0.03922  -0.0001   0.0809   0.9999
   7.750   0.8686   0.05178   0.04571  -0.0013   0.0813   0.9999
   8.000   0.8780   0.05788   0.05214  -0.0027   0.0822   0.9999
   8.250   0.8118   0.09388   0.08901  -0.0410   0.1567   0.9999
   8.500   0.8507   0.09482   0.09001  -0.0256   0.1507   0.9999
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