Aerodynamic layout and design method of standard model for hypersonic boundary layer transition research

Abstract

The invention discloses a standard model aerodynamic layout and a design method for hypersonic boundary layer transition research. The standard model aerodynamic layout includes a head ellipsoid head and a cone body, and the head ellipsoid head and the cone body have a smooth transition ; On the bottom surface profile of the cone body, the section corresponding to the leeward side is the upper half-section profile, the upper half-section profile is the linear combination of the elliptic curve and the CST curve superimposed, and the section corresponding to the bottom of the aircraft is the lower half-section profile, the lower profile The half-cut line is an elliptic curve. The present invention also provides a design method for the standard model aerodynamic layout for the study of hypersonic boundary layer transition, and this design method can be used to obtain the above standard model aerodynamic layout. The standard model aerodynamic layout provided by the present invention can have the typical characteristics of the aerodynamic layout of a real aircraft, and at the same time, the entire shape can be fully analytically described by mathematical expressions, so as to meet the simplified requirements for the aerodynamic layout of flight tests and numerical calculations.

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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