Wind tunnel air inlet duct test support with throttling and injection functions

Abstract

The invention relates to a wind tunnel air inlet test support with throttling and injection functions, and belongs to the field of test aerodynamics. Wherein the test model, the model outlet switching section, the closed throttling system, the bracket middle main body structure and the mixing section are coaxially butted in sequence and are horizontally positioned at the center line position of the wind tunnel test section; the sleeve sleeves the outer wall of the axial tail end of the middle main body structure of the bracket; the upper support arm of the bracket is vertically mounted at the top of the sleeve; the lower support arm of the bracket is vertically mounted at the bottom of the sleeve; the bracket upper support arm and the bracket lower support arm are symmetrically arranged relative to the sleeve; the invention provides a wind tunnel air inlet duct test support with throttling and ejection functions, which can be used for a 0.6 m magnitude high-speed wind tunnel, can adapt to outlet sizes of different air inlet ducts, has a throttling function, and can meet test flow requirements of low Mach number aircraft air inlet ducts, embedded air inlet ducts and other special air inlet ducts.

Description

technical field [0001] The invention belongs to the field of test aerodynamics, and relates to a wind tunnel air inlet test bracket with throttling and ejection functions. Background technique [0002] The air intake is one of the main components of the air-breathing aircraft, and its performance directly affects the overall performance of the engine and even the aircraft. The wind tunnel test is one of the main means to evaluate the performance of the intake port. [0003] For the aviation intake port test, the Mach number range is generally low, and the flow rate entering the intake port by ramming is small, which cannot meet the flow value required by the actual operation of the intake port. At this time, the working line of the intake port and the working line of the engine are If there is no intersection, the purpose of the intake port test cannot be achieved. In addition, in order to be stealthy and improve the penetration capability, some aircraft adopt the aerodyna...

AI Technical Summary

Problems solved by technology

However, for 0.6m level high-speed wind tunnels, due to the small space in the tunnel along the flow direction and vertical flow direction, it is difficult to arrange additional suction and injection devices in the tunnel without affecting the establishment of the flow field in the wind tunnel

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