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Ernest:
No need to look any further. I just read the article in Sport Aviation. It looks like an excellent article. The only problem is there was too little space alloted to such an important topic. The author should have had 10 times as much space to elaborate on his points.
Nonetheless, I believe that vortex generators can plausibly be added in front of either the inlet or outlet to optimize / control the boundary layer. The nice thing about vg s is that they can be easily moved around to optimize the design. Much better than cutting, shaping, and patching metal. I feel that with proper design these flush surface designs of in and out can provide the simplest and easiest cooling system with minimal compromise.
Regards;
James Freeman
Ernest Christley wrote:
James wrote:
Ernest, I did not see that specific paper. Do you know an easy to find it? Thanks.
Regards; James Freeman
Ernest Christley wrote:
James wrote:
Second point: I believe that a reversed direction NACA scoop would make an excellent low drag exit port for the cooling air stream. If anyone tries it, please let us know your findings.
According to the article, NACA tried it. It didn't work very well. A straight sided 'boxy' exit works much better.
The Sport Aviation article referred to it. I took the author's word for it because I seem to recall having read such a paper before. I would have to search the NACA site to find it again.
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