Slit parallel blowing method for drag reduction of hypersonic aircraft

A hypersonic and aircraft technology, applied in the direction of affecting the air flow flowing through the surface of the aircraft, drag reduction, aircraft parts, etc., can solve the problems that the frictional resistance of hypersonic aircraft cannot be effectively reduced, and achieve the reduction of hypersonic aircraft resistance and carrying weight Lightweight and economical
CN112758309APending Publication Date: 2021-05-07BEIHANG UNIV
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Patent Information

Authority / Receiving Office
CN ยท China
Current Assignee / Owner
BEIHANG UNIV
Publication Date
2021-05-07

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Abstract

The invention belongs to the field of aircraft design, and particularly relates to a slit parallel blowing method for drag reduction of a hypersonic aircraft; the method comprises the following steps: arranging slits on the windward side of an aircraft, and then blowing air into the boundary layer of the wall surface in parallel through the slits. A novel application scheme of the slit parallel blowing resistance reduction technology is provided for the hypersonic aircraft, the surface friction resistance of the hypersonic aircraft is reduced through the slit blowing technology, and meanwhile the torque characteristic of the hypersonic aircraft is not changed. Different from shock wave resistance reducing modes such as reverse jet flow and installation of a shock wave rod, the main implementation way of the invention is to reduce the frictional resistance of the surface of the hypersonic aircraft by adopting a slit parallel blowing mode, so that the purpose of reducing the total resistance of the aircraft is achieved.
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Description

technical field

[0001] The invention belongs to the field of aircraft design, in particular to a slit parallel blowing method that can be used for drag reduction of hypersonic aircraft. Background technique

[0002] When a hypersonic vehicle flies at high altitude at a high Mach number, the total resistance mainly includes shock wave resistance and frictional resistance. However, the current hypersonic vehicle drag reduction technology is mostly aimed at shock wave resistance, such as the common stagnation point reverse jet drag reduction and shock wave resistance. Rod drag reduction technology. Such as figure 1 As shown (see the literature "Chang Chaulyan. Effect of counterflow jet on a supersonic reentry capsule. AIAA 2006-4776, 2006" and "Gauer M, Paull A. Numerical investigation of a spiked blunt nose cone at hypersonic speeds. Journal of Spacecraft and Rockets, 2008 (3)"), the reverse jet flow at the head of the return cabin (figure (a) shows the flow field of the rev...

Claims

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