A wind tunnel test facility for the separation simulation of the cowling of an aspirated hypersonic vehicle

Abstract

The invention discloses a wind tunnel test facility for the separation simulation of the cowling of an aspirated hypersonic vehicle, comprising a model apparatus and a jet apparatus. Based on the ideaof integrative design, the requirements of model support, jet air supply, separation distance adjustment and securing the similarity of inter-stage area are comprehensively considered in the device;the designed modified aircraft precursor has the functions of model support, jet air supply and separation distance adjustment, and ensures the similarity of the shape of the inter-stage area. The designed gas supply adapter bar has the functions of model support and jet gas supply, and the whole test device is easy to assemble and disassemble, and is convenient to use. The wind tunnel test deviceof the invention solves the key technical problems such as model support, separation distance adjustment and reverse thrust jet simulation faced by the current experiment. The similarity of the fairing is ensured, and no additional hard-to-correct interference is introduced, and the reliable fairing aerodynamic load data is obtained under the interaction between the reverse jet and the incoming flow.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a wind tunnel test device used for separation simulation of an air-breathing hypervehicle fairing. Background technique [0002] The air-breathing hypersonic vehicle is powered by a scramjet engine and can fly at hypersonic speeds in the atmosphere. However, the scramjet engine can only be started under hypersonic conditions, and the best performance can only be achieved under the flight conditions at the design point. Therefore, it is necessary to use rockets to boost the air-breathing hypersonic vehicle to the design point flight conditions. [0003] During the boosting process of an air-breathing hypersonic vehicle before reaching the design point flight conditions, a swivel body fairing is used to protect the aircraft's precursor, air intake and related equipment from harsh environments such as aerodynamic force and aerodynamic heat. destruc...

AI Technical Summary

Problems solved by technology

In the test, the "zero-crossing" correction method is generally adopted, that is, the normal force coefficient and pitching moment coefficient at zero angle of attack are used as the increment caused by the interference of the web support plate, and are used to correct the normal force coefficient and pitching moment at other angles of attack coefficient, but the constant correction amount itself has a certain degree of error at a non-zero angle of attack, and its applicability is limited

If the conventional support method is used in the separation simulation test of the fairing of an air-breathing hypersonic vehicle, the interference effect of the reverse thrust jet will be coupled with the interference effect of the web support plate and cannot be distinguished, making it difficult to correct the influence of the web support plate interference or deduct

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