A Supersonic Jet Flow Device Realizing Two-fluid Mixing Disturbance
A supersonic, two-fluid technology, applied in the field of wind tunnel experiments, can solve the problems of inaccurate experimental results and normal shock waves at the inlet position, so as to improve the accuracy and ensure the effect of incoming flow pressure
Active Publication Date: 2019-09-03
ZHEJIANG UNIV
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Problems solved by technology
[0006] The invention provides a supersonic jet flow device for realizing two-fluid mixing and disturbance, so as to solve the technical problem that the normal shock wave is easy to appear at the entrance position of the existing supersonic jet flow device during the experiment, resulting in inaccurate experimental results
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[0036] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0037] refer to figure 2 and image 3 , a preferred embodiment of the present invention provides a supersonic jet flow device for realizing two-fluid mixing disturbance, which is used to place in a wind tunnel. The supersonic jet flow device includes a support body 1 and a jet flow arranged above the support body 1 Structure 2, the support body 1 is provided with a gas joint 10 on the outside, and an airflow channel 11 communicating with the gas joint 10 is provided inside, and the support body 1 is provided with a fixing part 12 for connecting and fixing with the support device (not shown); the jet flow The interior of the structure 2 is provided with a gas stabilizing chamber 20 communicat...
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The invention discloses a supersonic jet-flow device for realizing the double-fluid mixed disturbance. The device is arranged in a wind tunnel. The device comprises a supporting body and a jet-flow structure arranged above the supporting body. An air connector is arranged outside the supporting body. An airflow channel communicated with the air connector is arranged inside the supporting body. A fixed part used for being fixedly connected with a supporting device is arranged on the supporting body. An air stabilizing cavity communicated with the airflow channel, and a spraying pipe positionedbehind the air stabilizing cavity are formed in the jet-flow structure. The spraying pipe comprises a contraction part, a throat part and an expansion part, wherein the three parts are connected in sequence. The outlet of the expansion part is square. The jet-flow structure further comprises a wedge-shaped precursor positioned at the front end of the air stabilizing cavity and configured to rightface the outlet of a wind tunnel nozzle. The sharp end of the wedge-shaped precursor is located at the forefront end of the supersonic jet-flow device. According to the invention, the wedge-shaped precursor is positioned to right face the outlet of the wind tunnel nozzle during the process of the wind tunnel experiment. Therefore, the occurrence of normal shock waves to the incoming flow can be avoided. The pressure of the incoming flow is ensured to be accurate, and the accuracy of the experiment is improved.
Description
technical field [0001] The invention relates to the field of wind tunnel experiments, in particular to a supersonic jet flow device for realizing two-fluid mixing disturbance. Background technique [0002] For aerospace vehicles flying at supersonic or hypersonic speeds, sometimes in order to adjust the flight attitude or flight trajectory of the aircraft, a supersonic jet device is generally installed in the aircraft, and the thrust generated by the supersonic jet is used to change the flight attitude of the aircraft. At this time, the mainstream flow is supersonic or hypersonic, the jet flow is supersonic airflow, and the two high-speed airflows are mixed and flowed. Obviously, the study of supersonic mixed jet disturbance experiment has important scientific research and engineering application value in the aerospace field. [0003] The above experiments can be realized in a wind tunnel. The wind tunnel experiment refers to using a power device to drive a controllable airf...
Claims
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IPC IPC(8): G01M9/04
Inventor 陈伟芳赵文文吴昌聚杨华陈丽华
Owner ZHEJIANG UNIV