Transonic static aeroelastic and longitudinal aerodynamic characteristics of a low-aspect-ratio swept wing

Junli Wang

doi:10.1063/1.5087963

Abstract

Based on the CFD/CSD coupling method, the transonic static aeroelastic characteristics of the low-aspect-ratio swept wing was studied by numerical simulation. The Navier-Stokes equation was used as the fluid computational control equations. The flow field mesh deformation was performed using the Transfinite Interpolation method (TFI) method, and the data exchange on the CFD/CSD coupling interface was realized by the Constant Volume Transform (CVT) method. Based on the above method, the transonic static aeroelastic coupling calculation program was developed. The results of ONERA M6 wing static aeroelastic calculated by the coupling program were compared with wind tunnel test and reference results, and the effectiveness of the program was verified. Through numerical simulation, the influence of different angles of attack and Mach number on the static aeroelastic deformation and torsion angle of the wing are studied. Finally, by comparing the surface pressure cloud and pressure coefficient of the rigid wing and the elastic wing, the influence of static aeroelastic on the longitudinal aerodynamic characteristics and stability of the wing is mainly analyzed.

Highlights

The transonic static aeroelastic problem of aircraft has always been one of the important issues that must be considered in the design of aircraft, and many aircraft encounter various transonic static aeroelastic problems during design and even flight phases
In order to improve aerodynamics and combat performance, modern aircraft are generally moving toward light weight and high speed
The flow control equation is nonlinear due to the influence of shock wave and surface layer interference, and the nonlinearity of the flow equation leads to the failure of the classical linear static aeroelastic analysis method

Summary

Introduction

The transonic static aeroelastic problem of aircraft has always been one of the important issues that must be considered in the design of aircraft, and many aircraft encounter various transonic static aeroelastic problems during design and even flight phases. In order to improve aerodynamics and combat performance, modern aircraft are generally moving toward light weight and high speed. The effect of transonic static aeroelastic deformation on aircraft flight performance is becoming more and more serious.. The difficulty of transonic static aeroelastic analysis is mainly due to the complexity of transonic flow. It can be seen that in the modern aircraft design process, studying the transonic static aeroelastic analysis method and accurately predicting the response of the static aeroelastic structure under transonic speed is a technical difficulty that aircraft designers must consider

Methods

Results

Conclusion