# Minimum number of cells for aircrat cfd analysis

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 August 18, 2012, 23:13 Minimum number of cells for aircrat cfd analysis #1 Member   nauman hashmi Join Date: Jun 2012 Posts: 54 Rep Power: 7 Sponsored Links 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

 August 19, 2012, 04:53 #2 Senior Member   cfdnewbie Join Date: Mar 2010 Posts: 557 Rep Power: 13 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...

 August 19, 2012, 05:45 RE #3 Member   nauman hashmi Join Date: Jun 2012 Posts: 54 Rep Power: 7 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?

 August 19, 2012, 06:02 #4 Senior Member   cfdnewbie Join Date: Mar 2010 Posts: 557 Rep Power: 13 what Reynolds number? what mach number? turbulent? laminar? What effects are you interested in? is there separation? What scheme are you using? What grid?

 August 19, 2012, 06:04 RE #5 Member   nauman hashmi Join Date: Jun 2012 Posts: 54 Rep Power: 7 0.8 mach number, turbulent flow at 30000 feet. interested in aerodynamic loads on surface. not flow analysis.

 August 19, 2012, 06:09 #6 Senior Member   cfdnewbie Join Date: Mar 2010 Posts: 557 Rep Power: 13 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?"....

August 19, 2012, 07:41
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Quote:
 Originally Posted by cfdnewbie Is shock capturing available?
His mach number is 0.8 so no problem with shock.

 August 19, 2012, 07:59 #8 Senior Member   cfdnewbie Join Date: Mar 2010 Posts: 557 Rep Power: 13 if he does an airfoil calculation, 0.8 might be sufficiently high to produce shocks on the expansion side!

 August 19, 2012, 10:01 bit more detail #9 Member   nauman hashmi Join Date: Jun 2012 Posts: 54 Rep Power: 7 sir i would be using SA model. my grid is tetra-hdyron 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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