Inverted jet stream and orifice designing method capable of reducing drag and preventing heat for hypersonic flight vehicle

A technology of hypersonic speed and design method, applied in the direction of affecting the air flow flowing through the surface of the aircraft, aircraft parts, aircraft control, etc., can solve the problems that can not significantly improve the characteristics of drag reduction and heat protection, and achieve optimal drag reduction and heat protection characteristics, performance-enhancing effects

Active Publication Date: 2015-04-22
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0005] In order to improve the defect that the circular nozzle hole cannot significantly improve its drag reduction and heat protection characteristics, the present invention proposes a design method for the drag reduction and heat protection reverse jet flow nozzle hole of a hypersonic vehicle, which can well solve its shortcomings and realize its The purpose of efficient drag reduction and heat protection

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  • Inverted jet stream and orifice designing method capable of reducing drag and preventing heat for hypersonic flight vehicle
  • Inverted jet stream and orifice designing method capable of reducing drag and preventing heat for hypersonic flight vehicle
  • Inverted jet stream and orifice designing method capable of reducing drag and preventing heat for hypersonic flight vehicle

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Embodiment Construction

[0023] In the supersonic incoming flow, it is very complicated to adopt the flow mode of reverse jet flow, such as figure 1 As shown, it includes secondary compression shock wave 1, recirculation zone 2, jet layer 3, Mach disk 4, separation shock wave 5 and contact surface 6, of which 7 is the nozzle hole. m ∞ is the incoming Mach number, P 0∞ is the total pressure of incoming flow, M j is the jet Mach number, P 0j is the total jet pressure. The Mach disk 4 in the flow field balances the pressure of the jet flow and the pressure of the incoming flow after the bow shock wave, and forms a contact surface 6 at the outer end of the Mach disk 4. The reverse jet flow forms a recirculation area under the action of the incoming flow, and then attaches to the surface. The free flow forms a bow shock wave under the reverse action of the jet flow, and forms a secondary compression shock wave at the outer edge of the recirculation zone boundary. Due to the existence of the recircula...

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Abstract

The invention discloses an inverted jet stream and orifice designing method capable of reducing drag and preventing heat for a hypersonic flight vehicle, and particularly relates a practical designing method capable of reducing drag and protecting heat for an inverted jet stream of the hypersonic flight vehicle, and provides a designing method with an orifice of regular polygons. The method comprises: firstly, a nozzle area S is chosen according to a passivation radius R0; secondly, angle numbers n of the regular polygons are confirmed, when a ratio alpha of circumcircle radiuses R of the regular polygons and circle radiuses of inner corner points of the polygons with the R is confirmed, meanwhile, the numbers n of the polygons are confirmed, and the shapes of the nozzles of the regular polygons can be confirmed. According to the method, based on the same nozzle areas, the shapes of the regular polygons can be adjusted by controlling divergence angles of the regular polygons and the positions of inner corners, and the influence area of the jet stream on a flow field is controlled. By enlarging the influence area of the jet stream on the flow field, the performance of the hypersonic flight vehicle is improved, the characteristic of the optimal drag reduction and heat prevention is achieved and the technical support for the design of an air vehicle is provided.

Description

technical field [0001] The invention relates to the design of a drag reduction and heat protection scheme for a hypersonic aircraft, in particular to a practical design method for a hypersonic aircraft's reverse jet flow resistance reduction and heat protection, and the target object is the blunt head precursor of the hypersonic aircraft. Design method of anti-drag and anti-heat reverse jet nozzle hole for hypersonic vehicle Background technique [0002] With the development of aerospace technology, faster flight speed, longer flight distance, higher flight altitude, and larger flight field have become the goals that aerospace science and technology workers are constantly pursuing. Hypersonic vehicles will encounter great resistance during flight, and the main resistance comes from wave resistance. How to effectively reduce resistance has always been a concern of many researchers. [0003] When a hypersonic vehicle enters the atmosphere at a very high speed, drag reduction ...

Claims

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Application Information

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IPC IPC(8): B64C23/00
Inventor 黄伟王振国李世斌柳军金亮颜力
Owner NAT UNIV OF DEFENSE TECH
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