Set ONERA M6 Wing Initial Condition
For ONERA M6 Wing case at http://www.grc.nasa.gov/WWW/wind/val.../m6wing01.html, it sets the Initial Conditions to be:
Mach=0.8395, Pressure (psia)=45.82899 Temperature (R)=460.0 Angle-of-Attack (deg)=3.06 Angle-of-Sideslip (deg)=0.0
And in the document, it says that:
These corresond to a Reynolds number of 11.72 million based on the mean aerodynamic chord length. These conditions match the Mach number, Reynolds number, and angle-of-attack of test 2308 from the paper by Schmitt and Charpin in AGARD Report AR-138 referenced below. The static temperature was selected to be 460 degrees Rankine, which with the Mach and Reynolds number yielded a static pressure of 45.82899 psi.
My questions are:
1). How the Reynolds number of 11.72 million was calculated based on the mean aerodynamic chord length? What is the density is used in calculation? Simply air? and the Velocity =?
Note that the mean aerodynamic chord is 0.64607 meters.
2). Why the static temperature was selected to be 460 degrees Rankine? And how to yield a static pressure of 45.82899 psi. I tried to use 460 degrees Rankine, but could not get the answer.
3). The input uses the wall function keyword, which is to invoke wall function boundary conditions on viscous walls, using the White-Christoph law of the wall.
Any one knows what is the meaning of White-Christoph law of the wall?
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