Standard model aerodynamic layout for transition research of hypersonic boundary layer and design method

Abstract

The invention discloses a standard model aerodynamic layout for transition research of a hypersonic boundary layer and a design method. The standard model aerodynamic layout for transition research ofthe hypersonic boundary layer comprises a head ellipsoidal head and a cone body; the head ellipsoidal head and the cone body are in smooth transition with each other; one section, corresponding to the leeward side, on a bottom molded line of the cone body is an upper half molded line; the upper half molded line is linear combined overlapping of an elliptic curve and a CST curve; one section, corresponding to the bottom of an aircraft, on the bottom molded line of the cone body is a lower half molded line; and the lower half molded line is an elliptic curve. The invention further provides thedesign method of the standard model aerodynamic layout for transition research of the hypersonic boundary layer; and the design method of the standard model aerodynamic layout for transition researchof the hypersonic boundary layer can be used for obtaining the standard model aerodynamic layout. The standard model aerodynamic layout for transition research of the hypersonic boundary layer has theadvantages that the standard model aerodynamic layout has typical characteristics of a real aircraft aerodynamic layout, and meanwhile, the whole appearance can be completely analyzed and described by using a mathematical expression to satisfy simplifying demands of flight test and numerical calculation on the aerodynamic layout.

Description

technical field [0001] The invention relates to the aerodynamic layout and design method of a standard model used for the transition research of a hypersonic boundary layer. Background technique [0002] When an aircraft flies in the atmosphere and interacts with the air, the thin layer outside the wall—the boundary layer—plays the main role. Its thickness is usually on the order of millimeters to centimeters, and it needs to be observed by special means. The transition of boundary layer from laminar flow to turbulent flow is one of the core problems of fluid mechanics. There are huge differences between laminar flow and turbulent flow in terms of friction resistance, noise, heat transfer and mixing. For example, under hypersonic conditions, the friction resistance and heat flow of turbulent flow are usually 3-5 times that of laminar flow, which seriously affects the safety and performance of aircraft. Therefore, it is of great practical significance to study the key issues...

AI Technical Summary

Problems solved by technology

However, the flow phenomena and mechanisms involved in the hypersonic boundary layer transition process are very complex, and it is difficult to overcome the difficulties encountered in engineering practice only by a single research method. It is necessary to design a specific standard model flight shape, combined with theoretical analysis, numerical simulation, wind tunnel Comprehensive research on the shape of the standard mold by various means such as experiments

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