Minimum number of cells for aircrat cfd analysis
hi i want to know that what should be the minimum number of cells or element are required for cfd analysis of aircraft cfd. request quote any international standard.
regards 
that depends on so many boundary conditions and parameters that it is impossible to answer! you should provide more details on what you are interested in...

RE
i want to conduct cfd analysis in straight and level at one speed and one altitude. later on i have to conduct FSI. for accurate results what should be number of cells for this?

what Reynolds number? what mach number? turbulent? laminar? What effects are you interested in? is there separation? What scheme are you using? What grid?

RE
0.8 mach number, turbulent flow at 30000 feet. interested in aerodynamic loads on surface. not flow analysis.

so what scheme will you use? what order of spatial approximation? Is shock capturing available? What type of grid? can you adapt the grid during the computation? What is your Reynolds number (approx. ) ?
The question you are posing here is very general, it is like "how much do I need to spend for a car?".... :) 
Quote:

if he does an airfoil calculation, 0.8 might be sufficiently high to produce shocks on the expansion side!

bit more detail
sir i would be using SA model. my grid is tetrahdyron with prismatic boundary layer. i can use grid adaptation, i am using fluent and ansys for cfd and meshing respectively. my main aim is calculate the aerodynamic loads on the lifting body by using Fluid structure interaction.
regards 
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