Wide-speed-range air inlet channel design method based on double-incidence bending shock waves

Abstract

The invention discloses a wide-speed-range air inlet channel design method based on double-incidence bending shock waves. The method comprises the following steps of designing a double-incidence bending shock wave reference flow field based on the bending shock wave theory; designing an air inlet channel initial throat section molded line, and performing reverse flow streamline tracking in the reference flow field to obtain an initial air inlet channel compression molded surface; designing an air inlet channel isolation section outlet section, expanding an air inlet channel initial throat section in a double-S-bend form, and stretching in an equal-straight manner to obtain a three-dimensional inward-turning wide-speed-range air inlet channel isolation section; carrying out wall surface fairing and viscosity correction; taking the tail end of a first-stage compression molded surface of an air inlet channel as the rotating shaft position of a first-stage splitter plate, and taking the length of a second-stage compression molded surface as the length of the first-stage splitter plate; taking the position where the second derivative of an upper wall curve of the air inlet isolation section is zero, taking the position as the position of a second-stage splitter plate rotating shaft, and taking the length from the second-stage splitter plate rotating shaft to the air inlet channel initial throat section as the length of the second-stage splitter plate; and designing a discharge port area under the Mach number and a throat area under the Mach number. Expansion waves at the position of the rotating shaft can be eliminated; and performance requirements are met.

Description

technical field [0001] The invention relates to the field of air intakes of wide-speed range aircraft, in particular to a design method for wide-speed range air intakes based on double-incident curved shock waves. Background technique [0002] At present, wide-speed aircraft is a popular research topic in the world's aerospace powers, and it is also an important direction for future aircraft development. As the core component of the propulsion system, the air inlet is used to capture enough airflow for the engine while achieving high-efficiency compression to ensure that the entire propulsion system generates enough thrust to meet the aircraft's work in a wide speed range. According to different forms of incoming flow compression, the current hypersonic inlets mainly include: binary inlets, axisymmetric outer cone inlets, side pressure inlets and three-dimensional internal rotation inlets. types. Among them, the three-dimensional internal rotation inlet has the characteris...

AI Technical Summary

Problems solved by technology

At the same time, researchers generally use the traditional characteristic line method to carry out the reverse design of the reference flow field, which is not only complicated in programming, but also poor in stability, which limits the selection range of the reference flow field, thereby reducing the geometrical structure of the inlet.

It can be seen that one of the problems currently restricting the performance of the air intake of wide-speed aircraft is the lack of a design method for wide-speed air intakes based on double-incident bending shock waves.

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