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Aerodynamic shape design method of waverider in kiss-cut flow field with variable shock wave angle

A technology of aerodynamic shape and design method, applied in aircraft parts, ground installations, transportation and packaging, etc., can solve the problem of limited freedom of waverider shape design, achieve enhanced shape practicability, widen design freedom, and increase design Effects of degrees of freedom

Active Publication Date: 2018-02-23
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0007] The method for designing the aerodynamic shape of the waverider in the kiss-cut flow field with variable shock wave angle provided by the present invention solves the problem that when designing the waverider with the kiss-cut cone method in the prior art, only the same reference flow can be used in each kiss-cut plane. field, leading to technical problems that limit the freedom of waverider shape design

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  • Aerodynamic shape design method of waverider in kiss-cut flow field with variable shock wave angle
  • Aerodynamic shape design method of waverider in kiss-cut flow field with variable shock wave angle
  • Aerodynamic shape design method of waverider in kiss-cut flow field with variable shock wave angle

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Embodiment Construction

[0030] The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention.

[0031] The invention proposes a waverider design method for a kiss-cut flow field with variable shock wave angle. The method is an extension of the existing kiss-cut cone method, and improves the design freedom of the waverider when the shock angle changes.

[0032] see figure 2 , the waverider design method of variable shock wave angle kiss-cut flow field provided by the present invention comprises the following steps:

[0033] Step S100: Determine the basic profile of the waverider in the kiss-cut flow field with variable shock angle, and discretize the shock exit profile in the basic profile into several points;

[0034] like image 3 As shown, the...

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Abstract

The invention provides an aerodynamic configuration design method of a changeable-shock-angle osculating flow field wave rider. According to the aerodynamic configuration design method disclosed by the invention, a changing rule curve of a shock angle in an unfolding direction is shown in a parabola manner, and the situation that design is performed under the same shock angle is avoided, so that the obtained wave rider can concurrently meet requirements for the volume, the plot ratio and the lift-to-drag ratio, and the designing freedom degree of the wave rider is increased.

Description

technical field [0001] The invention relates to the technical field of aerodynamic shape design of a hypersonic vehicle, in particular to an aerodynamic shape design method for a waverider in a kiss-cut flow field with a variable shock wave angle. Background technique [0002] Whether a hypersonic vehicle has a high lift-to-drag ratio (that is, the ratio of lift to drag) during flight is an important indicator to measure the aerodynamic shape design of a hypersonic vehicle. The existing research results show that the waverider can well achieve good aerodynamic performance during hypersonic flight and ensure a high lift-to-drag ratio of the aircraft. The concept of waveriding was first proposed by Professor Nonweilwer in the 1950s. The existing design methods include wedge-guided method, cone-guided method and kiss-cut method. [0003] The wedge-shaped flow field required in the wedge guidance method can be obtained by solving the plane oblique shock wave relation. The refer...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00
CPCB64F5/00
Inventor 刘珍柳军丁峰黄伟陈韶华罗仕超符翔闻讯张宝虎
Owner NAT UNIV OF DEFENSE TECH
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