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Naca 0012 lift/drag values

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Old   August 6, 2006, 23:37
Default Naca 0012 lift/drag values
  #1
Raj
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Hello there, can anyone lemme know where I can kind lift/drag values for Naca 0012 airfoil at Re more than 500000....any angle of attack is fine with me...any paper citing from ur side would be of a great help...since I need them urgently
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Old   August 7, 2006, 20:45
Default Re: Naca 0012 lift/drag values
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pablo cornejo
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try using Xfoil code, it has good correlation with experimental data .
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Old   August 7, 2006, 20:47
Default Re: Naca 0012 lift/drag values
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Raj
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Actaully I need a published paper to validate my data....I know abt xfoil...but need a paper to compare....thanks anyway for replying
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Old   August 8, 2006, 03:26
Default Re: Naca 0012 lift/drag values
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James Date
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.J Thibert, M. Grandjacques, and L.H. Oham, "NACA 0012 Airfoil", AGARD Advisory Report, 1979.

N. Gregory and O.L. O'Reilly, "Low Speed Aerodynamic Characteristics of NACA0012 Airfoil Section, Including the Effects of Upper Surface Roughness Simulation Hoarfrost", NPL Aero Report 1308, National Physical Laboratory 1970.

I think one of the these reports will have what you are looking for.

Reagrds

James Date

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Old   August 9, 2006, 00:45
Default Re: Naca 0012 lift/drag values
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san
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Hi,

I am unable to solve the tutorial file given in fluent- aerofoil , compressible flow problem. Mach number=0.8.

I followed the instruction given in tutorial but i was unable to get the solution.

can you give your idea how to solve compressible flows.

bye san
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Old   August 9, 2006, 16:27
Default Re: Naca 0012 lift/drag values
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Raj
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Thanks Mr.James...thanks man...i will check out for that papers

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