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fluid properties for 0.15 mach number

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Old   April 28, 2015, 09:08
Default fluid properties for 0.15 mach number
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Aathavan
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Dear All,
I have a problem to get the fluid properties, I want to replicate some of the experimental work in CFD.

The work which I want to replicate is McGhee et al low speed aerodynamics characteristics of a 17 % thick airfoil.

In their work they used a range of Reynolds number vs angle of attack. How ever they mentioned that the lift and drag co efficients are function of Mach number.

The Mach numbers are 0.10 and 0.15, but I am wondering that how they calculated the Re number?

I have the following information, from the below information I need to calculate velocity.

Re range is = 2 *10^6 to 20*10^6

M = 0.15
Chord length = 58.42 cm


My questions are,

How can I get kinematic viscosity, density, and dynamic viscosity?


Thanks,
Aadhavan,
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Old   April 28, 2015, 12:21
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agd
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You are going to need more information. At a minimum you need a freestream temperature. With that you can compute the speed from the Mach number and estimate the viscosity from Sutherland's law. Then use the Reynolds number to get the density.
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