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HT22 (ht22-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HT22 (ht22-il)
Reynolds number: 100,000
Max Cl/Cd: 36.24 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht22-il-100000-n5.txt
Download as CSV file: xf-ht22-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6520   0.10873   0.10384   0.0359   1.0001   0.0449
  -8.250  -0.6497   0.10485   0.10001   0.0330   1.0001   0.0461
  -8.000  -0.6494   0.10099   0.09620   0.0274   1.0001   0.0475
  -7.750  -0.6449   0.09639   0.09163   0.0191   1.0001   0.0481
  -7.500  -0.6348   0.09119   0.08640   0.0117   1.0001   0.0483
  -7.250  -0.6233   0.08591   0.08104   0.0060   1.0001   0.0484
  -7.000  -0.6107   0.08069   0.07570   0.0016   1.0001   0.0485
  -6.500  -0.5851   0.06482   0.05967  -0.0026   1.0001   0.0271
  -6.250  -0.5721   0.06057   0.05537  -0.0040   1.0001   0.0264
  -6.000  -0.5548   0.05565   0.05030  -0.0066   1.0001   0.0258
  -5.750  -0.5344   0.05035   0.04474  -0.0093   1.0001   0.0256
  -5.500  -0.5108   0.04463   0.03858  -0.0118   1.0001   0.0264
  -5.250  -0.4859   0.03976   0.03315  -0.0132   1.0001   0.0271
  -5.000  -0.4620   0.03558   0.02852  -0.0140   1.0001   0.0271
  -4.750  -0.4368   0.03181   0.02424  -0.0144   1.0001   0.0271
  -4.250  -0.3847   0.02550   0.01697  -0.0145   1.0001   0.0281
  -4.000  -0.3586   0.02379   0.01507  -0.0145   1.0001   0.0301
  -3.750  -0.3314   0.02228   0.01328  -0.0143   1.0001   0.0333
  -3.500  -0.3036   0.02044   0.01108  -0.0138   1.0001   0.0350
  -3.250  -0.2759   0.01895   0.00930  -0.0133   1.0001   0.0367
  -3.000  -0.2495   0.01763   0.00801  -0.0130   1.0001   0.0413
  -2.750  -0.2226   0.01662   0.00691  -0.0126   1.0001   0.0461
  -2.500  -0.1961   0.01556   0.00584  -0.0121   1.0001   0.0513
  -2.250  -0.1694   0.01486   0.00511  -0.0117   1.0001   0.0607
  -2.000  -0.1427   0.01411   0.00436  -0.0113   1.0001   0.0735
  -1.750  -0.1159   0.01338   0.00376  -0.0110   1.0001   0.0975
  -1.500  -0.0896   0.01243   0.00330  -0.0109   1.0001   0.1909
  -1.250  -0.0687   0.01057   0.00309  -0.0099   1.0001   0.5984
  -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   0.1645   0.00968   0.00250  -0.0100   0.9553   0.9999
   1.000   0.2079   0.00988   0.00254  -0.0125   0.8440   0.9999
   1.250   0.2337   0.01024   0.00255  -0.0109   0.7373   0.9999
   1.500   0.2570   0.01066   0.00260  -0.0093   0.6520   0.9999
   1.750   0.2818   0.01107   0.00269  -0.0082   0.5847   0.9999
   2.000   0.3073   0.01145   0.00282  -0.0075   0.5303   0.9999
   2.250   0.3333   0.01182   0.00297  -0.0069   0.4843   0.9999
   2.500   0.3597   0.01217   0.00316  -0.0064   0.4433   0.9999
   2.750   0.3860   0.01254   0.00339  -0.0060   0.4053   0.9999
   3.000   0.4125   0.01289   0.00362  -0.0057   0.3679   0.9999
   3.250   0.4390   0.01325   0.00386  -0.0054   0.3307   0.9999
   3.500   0.4655   0.01365   0.00413  -0.0051   0.2922   0.9999
   3.750   0.4920   0.01407   0.00446  -0.0048   0.2525   0.9999
   4.000   0.5184   0.01455   0.00482  -0.0046   0.2125   0.9999
   4.250   0.5446   0.01512   0.00524  -0.0045   0.1749   0.9999
   4.500   0.5708   0.01576   0.00577  -0.0043   0.1432   0.9999
   4.750   0.5969   0.01647   0.00642  -0.0041   0.1173   0.9999
   5.000   0.6228   0.01725   0.00716  -0.0039   0.0996   0.9999
   5.250   0.6485   0.01805   0.00794  -0.0037   0.0854   0.9999
   5.500   0.6742   0.01892   0.00888  -0.0034   0.0756   0.9999
   5.750   0.6992   0.01996   0.00996  -0.0030   0.0690   0.9999
   6.000   0.7247   0.02087   0.01100  -0.0027   0.0621   0.9999
   6.250   0.7491   0.02206   0.01220  -0.0024   0.0572   0.9999
   6.500   0.7742   0.02335   0.01373  -0.0019   0.0538   0.9999
   6.750   0.7988   0.02473   0.01534  -0.0015   0.0507   0.9999
   7.000   0.8226   0.02605   0.01671  -0.0012   0.0473   0.9999
   7.250   0.8462   0.02785   0.01879  -0.0008   0.0445   0.9999
   7.500   0.8694   0.03001   0.02135  -0.0004   0.0426   0.9999
   7.750   0.8912   0.03248   0.02425   0.0000   0.0408   0.9999
   8.000   0.9120   0.03482   0.02699   0.0002   0.0389   0.9999
   8.250   0.9320   0.03664   0.02898   0.0003   0.0368   0.9999
   8.500   0.9479   0.04004   0.03275   0.0002   0.0353   0.9999
   8.750   0.9589   0.04469   0.03812  -0.0001   0.0345   0.9999
   9.000   0.9627   0.05051   0.04460  -0.0013   0.0339   0.9999
   9.250   0.9574   0.05746   0.05209  -0.0040   0.0337   0.9999
   9.500   0.9422   0.06563   0.06065  -0.0093   0.0338   0.9999
   9.750   0.9180   0.07678   0.07195  -0.0210   0.0343   0.9999
  10.000   0.8961   0.08902   0.08417  -0.0309   0.0347   0.9999
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