Binary hypersonic variable geometrical inlet channel, design method and work mode

Abstract

The invention relates to a binary hypersonic variable geometrical inlet channel, a design method and a work mode, belonging to the field of the aerodynamic design of the inlet channels. The inlet channel comprises a compression surface, an inner contraction section of the inlet channel, a straight distance section and a lip cover; wherein the lip cover is of the structure capable of moving front and back in parallel along the incoming flow direction. By moving the simple lip cover front and back in parallel along the incoming flow direction, the inlet channel can realize the regulation from a closed state to an opening state, the regulation of the internal contraction ratio of a high-march number state and a lower-march number state, and the regulation of the flow capture under the condition of different coming flows in a normal operation range.

Description

technical field [0001] The invention relates to a binary hypersonic variable-geometry inlet, a design method and a working mode, and belongs to the field of aerodynamic design of the inlet. technical background [0002] For an air-breathing aircraft, the excellent aerodynamic performance of the inlet in the design state cannot guarantee its normal and stable operation under all key operating states. Especially for a hypersonic air-breathing aircraft operating in a wide Mach number range, when it is in a non-design operating state, can the inlet provide enough air for the engine to meet certain airflow quality requirements with less resistance and flow loss? The flow rate will be an important criterion for evaluating the comprehensive aerodynamic performance of the intake port. [0003] The subsonic inlet used in low-speed aircraft is relatively simple to match the engine flow. When the flight state changes, the inlet can automatically adjust the relationship between the fre...

AI Technical Summary

Problems solved by technology

[0005] From the analysis of the data already available, it can be found that a large number of variable geometry inlet schemes only focus on solving a single problem, such as low Mach number flow capture or low Mach number start-up, and the schemes do not solve low Mach at the same time

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