Stagnation Point Releif

[CraigBEng]

Hi would like some info, sorry if it is basic!?

what is a stagnation point?

where is it located on a NACCA 23015?

I am currently doing a project to use the energy at the stagnation point by means of a slat that runs from the leading edge on top of an aerofoil, releasing it at the trailing edge this in theory should reduce drag by reducing the wake region area, increase lift, greater stall angle, and reduce turbulent flow (boundary layer).

Please note I am a "Newbie" could anyone please point me in the direction of some research that has been done of a simular kind or offer any help? as it is difficult to find any?
Anyone that would like to throw some ideas to improve or critisize my project please do. i can send pictures of the prototype aerofoil.

Thank you

Craig Murray

 

[GregLocock]

The stagnation point is the point on the nose of the airfoil at which there is no surface velocity, or, if you like, where the airstream splits between the top and the bottom surfaces.

It moves around.



Cheers

Greg Locock

Please see FAQ731-376 for tips on how to make the best use of Eng-Tips.

 

[CraigBEng]

Thank you for your reply,

Yes i found through research it is the point of maximum pressure on the aerofoil.
i was wontering what would happen in i was to introduce a secondary thin aerofoil over the top of the original think it is a NACCA 38015. clearance is just a couple of mm.

any one know how to find the stagnation point at the leading edge of an aerofoil?

i attend to use the stagnation point flow and release it at the trailing edge via the secondary air flow.
what would be the advantages and disadvantages of doing this?