Quote:
Originally Posted by Bicycle Bob
"If it's a 'laminar' aircraft you can increase the Cd significantly,as it is not possible to have laminar flow above critical Reynolds number in ground-effect.( 20-mph up )."
Do you have a reference, or a rationale for that? Thanks.
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Bob,just now catching your post.Am away from my references here at the copy center so relying on memory ( a scary proposition!),here's what I recall.
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A laminar structure is designed to operate under 'flight conditions' which for aircraft is at altitude,in free-flow environment,with turbulent-free air.
A laminar structure is only 'laminar' up to the first point of minimum pressure ( center of lift ) after which the flow is necessarily turbulent due to the un-favorable pressure gradients present.
Also,in aircraft applications,drag is customarily governed by skin friction and embody zero flow separation,whereas in automotive applications,skin friction plays an insignificant role,with flow separation responsible for the largest portion of drag.
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For road vehicles above 20-mph,and for the surface roughness conditions obtainable in automotive finishes ( or even polished surfaces ) the given surface grain size versus vehicle length/velocity relationship mandates that the Reynolds number go 'critical' and boundary layer transition to ' turbulent' with a ground/air velocity of 20-mph.Which is all good for road vehicles,as the turbulent boundary layer allows the separation point to be moved rearward,allowing pressure regain and reduction of pressure drag,the largest component of profile drag.
All air in ground proximity is considered turbulent and cannot support the environment necessary for laminar boundary layer,unless the velocity is held below 20-mph.( i.e. college teams pulling off 7,000 mpg as they creep along a closed-course ).
From memory,I will credit references I cited in my stickys: Fluid Mechanics by Dauherty and Franzini,Boundary Layer Theory by Schlichting,Aerodynamic Drag by S. Hoerner, Theoretical Aerodynamics ( can't remember author ),I think that Abbott and Von Doenhoff get into it also in their Theory of Wing Sections.
In my Fluids text there were some sample problems for road vehicles.Critical Rn occurred around 500,000 which was triggered at very low ground velocity.
That's all I can do off the top of my head.
At Battle Mountain I grilled the Cal Poly team( I think it was).They were using CFD for engineering their bike and believed that Cd 0.11 was probably the 'range' for bikes running,like Varna Diablo III.The day I was there,Sam went 81.6-MPH in it.
Matt Llewelyn's (sp?) Sylph was designed around something like a Cd 0.0066 laminar wing section and also scored Cd 0.11,in ground proximity in the Guggenheim tunnel at Cal Tech.
It appears that,on the ground, the 'laminar' forms cannot exploit the efficiencies they enjoy in free flight.