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Boundary layer guide and suction combined hypersonic air inlet flowing control method

A hypersonic, flow control technology, applied in the direction of boundary layer control, air inlet combustion of power plant, aircraft control, etc., it can solve the problem that the boundary layer cannot be discharged to the bottom side, and the suction hole cannot play a good role in suction. and other problems to achieve the effect of effective suction

Active Publication Date: 2019-04-19
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

The scheme of arranging the suction hole on the bottom side of the bump takes into account the accumulation of the boundary layer on the bottom side of the bump, so the boundary layer is pumped away through the suction hole. This scheme is suitable for supersonic bumps with strong boundary layer displacement. However, under hypersonic conditions, the Bump surface often cannot move most of the boundary layer to the bottom side, so the suction hole cannot play a good role in suction

Method used

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  • Boundary layer guide and suction combined hypersonic air inlet flowing control method
  • Boundary layer guide and suction combined hypersonic air inlet flowing control method
  • Boundary layer guide and suction combined hypersonic air inlet flowing control method

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Embodiment 1

[0026] see Figure 1-5 , an embodiment of the present invention provides a hypersonic inlet flow control method combining boundary layer guidance and suction, including the following steps:

[0027] Step 1, forming a boundary layer guide surface on the hypersonic inlet precursor, thereby generating a lateral pressure gradient on the boundary layer guide surface, and changing the flow direction of the airflow passing through the boundary layer guide surface through the lateral pressure gradient Orientation change;

[0028] With the help of the working principle of the supersonic bump, the flow direction of the airflow flowing through the boundary layer guiding surface is changed, and the precursor surface generates a lateral pressure gradient, thereby actively guiding the boundary layer airflow. The guiding direction can be predetermined, theoretically Any direction can be used, and it can also be set or obtained by analysis according to actual design conditions. The boundary...

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Abstract

The invention discloses a boundary layer guide and suction combined hypersonic air inlet flowing control method. The method includes steps: forming a boundary layer guide profile on a hypersonic air inlet precursor, and enabling directional changing of a flowing direction of an airflow flowing through the boundary layer guide profile through a transverse pressure gradient generated on the boundarylayer guide profile; controlling the transverse pressure gradient acting on the boundary layer guide profile to guide a boundary layer to a local part of the boundary layer guide profile; and providing the local part of the boundary layer guide profile with a suction hole. By adoption of the scheme, the problem of low suction performances in the prior art is solved, targeted suction is realized,and the suction performance is improved.

Description

technical field [0001] The invention relates to the technical field of hypersonic inlets, in particular to a hypersonic inlet flow control method combining boundary layer guidance and suction. Background technique [0002] Boundary layer pumping is considered to be a very effective method of controlling the flow in the inlet boundary layer. Boundary layer suction means that a suction hole is set on the wall surface, and the boundary layer airflow is drawn out through the pressure difference at both ends of the hole, thereby making the boundary layer thinner. The boundary layer suction is composed of a suction hole, a suction chamber and a discharge system. The working process is that the boundary layer enters the suction chamber through the suction hole, and then is discharged through the discharge system. The suction greatly reduces the thickness of the boundary layer, and the quality of the airflow captured by the inlet is improved; on the other hand, due to the thinning ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02B64F5/00B64C30/00
CPCB64C30/00B64C2230/00B64D33/02B64F5/00
Inventor 王翼徐尚成王振国范晓樯苏丹赵星宇闫郭伟
Owner NAT UNIV OF DEFENSE TECH
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