Variable cross-section high supersonic speed inward rotation type air inlet with consistency of local contraction ratio

Abstract

The invention discloses a variable cross-section high supersonic speed inward rotation type air inlet with consistency of local contraction ratio, which comprises an air intake contraction section and an isolation segment which are successively connected, the air intake contraction section has an inlet and an outlet, the invention is characterized in that the formation of the air intake contraction section has a gradually contracted shape from the inlet to the outlet, a three-dimensional flow field of the air intake contraction section forms two or more than two sub-flow pipes along an axial direction of the air intake contraction section, the sub contraction ratio of the inlet and the outlet of each sub-flow pipe is substantially equal to the total contraction ratio of the inlet and the outlet of the air intake contraction section, and each sub-flow pipe forms a part of the axisymmetric internal contraction flow field. The invention also discloses a design method of the variable cross-section high supersonic speed inward rotation type air inlet with consistency of local contraction ratio. Under designed Mach number, the initial shock wave encloses a front rim of the air intake, the full flow capture can be realized, and the intersection of initial lines of the reflection shock wave and the isolation segment realizes the wave absorption.

Description

technical field [0001] The invention belongs to the field of hypersonic air inlets, in particular to hypersonic variable cross-section air inlets. Background technique [0002] The hypersonic inlet is a key component of the hypersonic air-breathing engine, and its function is to capture the incoming air and compress it to the high-pressure and low-velocity state required by the combustion chamber. Its design goal is to have the largest possible mass capture rate and complete the compression of the incoming flow with the smallest possible flow loss. The typical design requirements of hypersonic inlets have the following points: (1) As high as possible mass capture rate, under the same capture area, more flow can be provided for the combustion chamber while reducing overflow resistance; (2) High compression efficiency and better flow quality; (3) Wide Mach number working range, with automatic overflow capability at low Mach number and low self-starting Mach number; (4) Easy t...

AI Technical Summary

Problems solved by technology

The kiss-tangential axisymmetric method has significantly increased the design freedom because it gets rid of the limitation that all streamlines are from the same reference flow field, but by adopting a series of axisymmetric reference flow fields that are coaxial and have the same generatrix, they also face the inlet / The problem that the difference in export aspect ratio cannot be too large, otherwise the position of the axis of symmetry will be difficult to select

In addition, this method does not deal with the reflected shock wave. The position where the airflow reaches the reflected shock wave is not synchronized. There is no guarantee that there will be no lateral flow after the reflected shock wave. After the reflected shock wave, there are multiple shock wave reflections in the isolation section. , no longer has the homogeneity of the reflected shock front

Images