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HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il)
Reynolds number: 50,000
Max Cl/Cd: 16.38 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1430-il-50000.txt
Download as CSV file: xf-hs1430-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-430 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.7424   0.11747   0.10954   0.0199   1.0000   0.3502
  -6.500  -0.7716   0.11161   0.10360   0.0233   1.0000   0.3472
  -6.250  -0.8149   0.10448   0.09635   0.0280   1.0000   0.3450
  -6.000  -0.8686   0.09644   0.08807   0.0339   1.0000   0.3431
  -5.750  -0.9041   0.09016   0.08149   0.0388   1.0000   0.3430
  -5.500  -0.9237   0.08542   0.07647   0.0426   1.0000   0.3439
  -5.250  -0.9348   0.08162   0.07236   0.0457   1.0000   0.3454
  -5.000  -0.9402   0.07856   0.06895   0.0484   1.0000   0.3475
  -4.750  -0.9401   0.07611   0.06620   0.0506   1.0000   0.3497
  -4.500  -0.9301   0.07417   0.06429   0.0517   1.0000   0.3527
  -4.250  -0.9186   0.07300   0.06312   0.0529   1.0000   0.3557
  -4.000  -0.9063   0.07212   0.06224   0.0539   1.0000   0.3592
  -3.750  -0.8950   0.07119   0.06124   0.0549   1.0000   0.3628
  -3.500  -0.8840   0.07024   0.06017   0.0560   1.0000   0.3667
  -3.250  -0.8707   0.06942   0.05916   0.0565   0.9994   0.3706
  -3.000  -0.8423   0.06950   0.05894   0.0543   0.9939   0.3752
  -2.750  -0.8127   0.06996   0.05922   0.0519   0.9890   0.3799
  -2.500  -0.7863   0.06981   0.05917   0.0503   0.9811   0.3850
  -2.250  -0.7511   0.07126   0.06061   0.0472   0.9744   0.3913
  -2.000  -0.7204   0.07157   0.06085   0.0449   0.9632   0.3975
  -1.750  -0.6908   0.07199   0.06110   0.0427   0.9509   0.4040
  -1.500  -0.5784   0.07199   0.06111   0.0289   0.8758   0.4181
  -1.250  -0.5058   0.07092   0.05993   0.0222   0.8348   0.4314
  -1.000  -0.4531   0.07005   0.05902   0.0184   0.8103   0.4427
  -0.750  -0.3970   0.06945   0.05854   0.0141   0.7919   0.4564
  -0.500  -0.3729   0.06911   0.05810   0.0141   0.7746   0.4672
  -0.250  -0.3471   0.06905   0.05829   0.0139   0.7585   0.4788
   0.000  -0.2836   0.06852   0.05786   0.0086   0.7479   0.5011
   0.250  -0.2711   0.06873   0.05829   0.0103   0.7292   0.5156
   0.500  -0.1995   0.06760   0.05747   0.0046   0.7212   0.5540
   0.750  -0.1958   0.06787   0.05809   0.0080   0.7003   0.5812
   1.000  -0.1746   0.06779   0.05858   0.0097   0.6830   0.6388
   1.250  -0.0644   0.06877   0.06062   0.0023   0.6709   0.8202
   1.500   0.0747   0.07299   0.06471  -0.0121   0.6471   0.8939
   1.750   0.3199   0.07165   0.06299  -0.0425   0.6404   0.9423
   2.000   0.4181   0.07085   0.06207  -0.0537   0.6191   0.9669
   2.250   0.6850   0.06135   0.05218  -0.0901   0.6165   0.9976
   2.500   0.6875   0.06158   0.05231  -0.0868   0.5948   1.0000
   2.750   0.8196   0.05466   0.04491  -0.1031   0.5891   1.0000
   3.000   0.7607   0.05755   0.04785  -0.0898   0.5691   1.0000
   3.250   0.7616   0.05788   0.04807  -0.0861   0.5554   1.0000
   3.500   0.8018   0.05622   0.04619  -0.0883   0.5447   1.0000
   3.750   0.8432   0.05494   0.04466  -0.0910   0.5350   1.0000
   4.000   0.7800   0.05853   0.04838  -0.0779   0.5240   1.0000
   4.250   0.8892   0.05429   0.04367  -0.0907   0.5168   1.0000
   4.500   0.8149   0.05829   0.04786  -0.0758   0.5094   1.0000
   4.750   0.5986   0.07387   0.06395  -0.0474   0.4957   1.0000
   5.000   0.6966   0.06698   0.05674  -0.0539   0.4941   1.0000
   5.250   0.9167   0.05660   0.04560  -0.0801   0.4904   1.0000
   5.500   0.2842   0.11176   0.10227  -0.0235   0.4831   1.0000
   5.750   0.1110   0.13142   0.12237  -0.0182   0.5741   1.0000
   6.000   0.1408   0.13255   0.12335  -0.0184   0.5666   1.0000
   6.250   0.1708   0.13528   0.12593  -0.0192   0.5635   1.0000
   6.500   0.2346   0.12489   0.11519  -0.0151   0.4871   1.0000
   6.750   0.2417   0.12742   0.11766  -0.0144   0.4889   1.0000
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