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

Pending Publication Date: 2021-05-07
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this device cannot effectively reduce the frictional resistance of hypersonic vehicles

Method used

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  • Slit parallel blowing method for drag reduction of hypersonic aircraft
  • Slit parallel blowing method for drag reduction of hypersonic aircraft
  • Slit parallel blowing method for drag reduction of hypersonic aircraft

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Embodiment Construction

[0025] The present invention will be further described below in conjunction with the accompanying drawings and examples. It should be understood that the following examples are intended to facilitate the understanding of the present invention, and have no limiting effect on it.

[0026] The slit blowing method for drag reduction of a hypersonic vehicle in this embodiment includes the following steps:

[0027] Step 1: Select the appropriate slit depth, slit blowing parameters, etc.

[0028] In this embodiment, a typical hypersonic vehicle with a waverider shape is selected. This shape has a pointed head and has the characteristics of small shock wave resistance and large frictional resistance when flying at high altitudes at high Mach numbers. The slit parallel air blowing device is suitable for on this aircraft. Considering that some structures on the shape of the aircraft have little effect on the wall friction and heat flow of the aircraft, the aircraft is simplified to a c...

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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.

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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Application Information

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IPC IPC(8): B64C21/04
CPCB64C21/04Y02T50/10
Inventor 高振勋莫凡韩冰蒋崇文李椿萱
Owner BEIHANG UNIV
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