A Wind Tunnel Test System for Vector Propulsion Aircraft Models

Abstract

The invention discloses a wind tunnel experiment system used for a vector-boosting airplane model. A first vector propulsion spray pipe and a second vector propulsion spray pipe are arranged in the machine body of the vector-boosting airplane model; the wind tunnel experiment system comprises a support pillar, a supporting rod used for supporting the vector-boosting airplane model, a compressed air source arranged outside the wind tunnel, as well as a first pipeline and a second pipeline; the first pipeline and the second pipeline are used for connecting the compressed air source with the first vector propulsion spray pipe and the second vector propulsion spray pipe. The wind tunnel experiment system has the advantages that high-pressure air in the compressed air source is released to the vector propulsion spray pipes through pipelines, so as to obtain air blast power, simulate the air blast state of a vector propulsion engine, and overcome the defect that in the prior art, the aerodynamics state of the vector propulsion airplane model cannot be simulated in a wind tunnel.

Description

technical field [0001] The invention relates to an aviation aerodynamic test equipment, in particular to a wind tunnel test system which can be used for a vector propulsion aircraft model. Background technique [0002] The wind tunnel test is based on the principle of aerodynamics, fixing the aircraft model or its parts, such as the fuselage, wings, etc. Flight status, get test data. The wind tunnel is the most basic test equipment for aerodynamic research and aircraft development. The development of each new type of aircraft requires a large number of tests in the wind tunnel. The main purpose of the wind tunnel test is to obtain the variation law of various aerodynamic parameters of the aircraft model. To evaluate the flight performance of each aircraft, in addition to factors such as speed, altitude, aircraft weight and engine thrust, one of the most important criteria is the aerodynamic performance of the aircraft. The aircraft wind tunnel test needs to support the en...

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Problems solved by technology

[0007] The wind tunnel test system for the vector propulsion aircraft model of the present invention can flexibly control the airflow velocity through the flow velocity control device, can simulate the jet state of the vector propulsion engine, and overcomes the inability of the prior art to simulate the air of the vector propulsion aircraft model in the wind tunnel Defects in the dynamic state can be simulated in the dynamic state with propulsion, greatly reducing the number of wind tunnel tests, the wind tunnel test is closer to the real state, and the accuracy of the results is higher

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