高超声速变体飞行器宽速域气动特性研究OACSTPCD

Wide-speed range flight is a critical design objective and development direction for hypersonic vehicles.However,the complex environmental changes pose design conflicts for fixed-configuration vehicles under different flight conditions.Hypersonic morphing vehicles can adapt to various flight conditions and meet performance requirements by presenting different configurations.This paper introduces numerical simulations to investigate the aerodynamic characteristics of a foldable-wing vehicle,and focuses on the lift-to-drag ratio,longitudinal static stability,and directional static stability of the aerodynamic configuration in different wing folding states at various flight altitudes and Mach numbers.The impact of varying wing folding angles(0°,45°,90°)on the aerodynamic performance are compared.The results indicate that across the entire range of speeds studied(Ma=0-5),the smaller wing folding angles result in the higher lift coefficients,drag coefficients,and lift-to-drag ratios.The wing folding angle of 0° exhibits the highest lift-to-drag ratio.In terms of longitudinal stability,the configuration with a smaller folding angle has better longitudinal stability.As the Mach number increases,the differences in longitudinal stability between different folding angles initially decrease and then increase.The static stability margins change from 1∶0.95∶0.84 to 1∶0.98∶0.88,then to 1∶0.89∶0.79.In addition,configurations with larger wing folding angles exhibit better directional stability.All three wing folding configurations are directionally stable during the low-speed flight phase.As the Mach number increases,the 0° and 45° folding angles gradually become directionally unstable.