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Internal waverider hypersonic inlet and design method based on random shock form

A technology of hypersonic speed and design method, which is applied to the air inlet of turbine/propulsion device, combustion air/combustion-air treatment, engine components, etc. It can solve the problems of the shape restriction of the inlet and outlet of the inlet and improve the aerodynamic force of the outlet. performance, improving low Mach number starting performance, and reducing windward external resistance

Inactive Publication Date: 2010-06-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In addition, the existing three-dimensional retractable inlet design generally adopts the direct streamline tracking technology in the same rotary basic flow field (which can be axisymmetric flow field or non-axisymmetric flow field). The shape of the exit is usually limited, and the initial incident shock wave can only be a regular arc shape
Although the variable center body radius design method of the non-axisymmetric flow field can customize the shape of the inlet and outlet of the inlet, which greatly improves the limitations of the shape design of the inlet, but it still cannot fundamentally solve the problem of arbitrary shock wave transverse design. cross-sectional shape problem

Method used

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  • Internal waverider hypersonic inlet and design method based on random shock form
  • Internal waverider hypersonic inlet and design method based on random shock form
  • Internal waverider hypersonic inlet and design method based on random shock form

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Embodiment 1

[0036] At the flow Mach number 6.0, the design is as follows figure 1 The axisymmetric internal contraction basic flow field is shown. The internal contraction rotary wall is composed of ICFA flow field and part of Busemann flow field. The flow field exit Mach number is designed to be 3.0, the area contraction ratio is 10.65, and the corresponding side length contraction ratio is 3.26.

[0037] The design requirements for the shape of the air inlet are: the inlet of the air inlet is a square (such as figure 2 ), each center of curvature of the shock wave is located on the lower base of the square, and the two sides are required to shrink toward the same center of curvature, while the upper wall shrinks toward a series of centers of curvature evenly distributed in the direction of curvature. Therefore, the shape of the shock wave and even the shrinkage ratio of the intake port are uniquely determined by the shrinkage ratio control angle α. When the contraction ratio control a...

Embodiment 2

[0040] At the flow Mach number 6.0, the design is as follows figure 1 The axisymmetric internal contraction basic flow field is shown. The internal contraction rotary wall is composed of ICFA flow field and part of Busemann flow field. The flow field exit Mach number is designed to be 3.0, the area contraction ratio is 10.65, and the corresponding side length contraction ratio is 3.26.

[0041] The design requirements for the shape of the air inlet are: the inlet of the air inlet is semicircular (such as Figure 4 ), each center of curvature of the shock wave is located on the outer circumference of the circle, requiring that the diameter of the semicircle shrinks toward the same center of curvature, while the circumferences on both sides shrink toward a series of centers of curvature evenly distributed in the direction of curvature. At this time, the shape of the shock wave and even the shrinkage ratio of the inlet port are controlled by the direction angle of the curvature o...

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Abstract

The invention provides an internal waverider-derived hypersonic inlet based on arbitrary shockwave shape and a design method thereof. The structure of the internal waverider-derived hypersonic inlet comprises an inlet contraction section and an inlet insulation section; wherein the inlet contracting section is inward contracted in three-dimension; hypersonic velocity incoming flow forms irregularinitial incident three-dimensional shockwave at the inlet; and the shockwave closes the three-dimensional inlet surface completely. The design method comprises the following steps: an internally contracted axisymmetric basic flow field used as a base is formed by the combination of ICFA flow field and partial Buesemann flow field; and after shapes of shockwave sections with different centers of curvature and directions of curvature are appointed, flown line tracing of the basic flow field with different centers and different radial positions is carried out on a plane in each circle of the hypersonic inlet to obtain the internal waverider-derived hypersonic inlet based on arbitrary shockwave shape. The internal waverider-derived hypersonic inlet and the method have the advantages of ensuring that the hypersonic inlet captures the incoming flow in full flow, increasing thrust force of an engine while reducing overflow resistance, improving pneumatic performance of an outlet of the hypersonic inlet, reducing windward external resistance of the hypersonic inlet, and improving starting performance of low-mach number of the hypersonic inlet.

Description

technical field [0001] The invention relates to an internal waveriding hypersonic inlet based on an arbitrary shock wave shape and a design method thereof, belonging to the technical field of hypersonic inlets. Background technique [0002] Hypersonic flight refers to flight with a Mach number greater than 5. Because of its important strategic significance, the research on hypersonic long-range maneuvering aircraft has become a hot research issue that the world's powers are competing to carry out. The air intake is the main component of the hypersonic propulsion system, and unlike traditional aircraft, the working principle of the hypersonic air intake is to use the ramming effect of the high-sound incoming flow to compress the airflow and provide an air source for the downstream components of the propulsion system . Therefore, the hypersonic air inlet is usually arranged at the front of the aircraft, which is completely integrated with the shape of the front body and desi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04
Inventor 尤延铖黄国平郭军亮朱呈祥梁德旺
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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