高超声速转捩研究飞行器(Hypersonic Transition Research Vehicle,HyTRV)是为研究高超声速复杂三维边界层转捩而设计的升力体标模,其外形更接近真实飞行器。为深入认识HyTRV边界层稳定性特征及转捩机制,验证数值模拟和理论分析结果,本...高超声速转捩研究飞行器(Hypersonic Transition Research Vehicle,HyTRV)是为研究高超声速复杂三维边界层转捩而设计的升力体标模,其外形更接近真实飞行器。为深入认识HyTRV边界层稳定性特征及转捩机制,验证数值模拟和理论分析结果,本文在马赫数6常规风洞中,采用红外热成像技术和高频压力传感器,获得了0°和2°攻角时HyTRV标模下表面(迎风面)的边界层转捩阵面及不稳定波的演化特征,并与一维稳定性分析结果进行了对比。研究结果表明:攻角为2°时,标模下表面的横流失稳区较0°攻角时范围缩小且位置后移,标模中心线处转捩早于两侧横流区。另外,横流区存在宽频的高频信号,信号幅值在转捩完成前达到饱和。该信号包含多频段扰动,多种扰动之间相互作用导致频谱变宽,最终促使边界层转捩变为湍流。展开更多
Focusing on the unclear mechanism of aerodynamic interference in overlapping rotors of heavy-load electric vertical take-off and landing(eVTOL)aircraft,this paper aims to reveal the aerodynamic interference characteri...Focusing on the unclear mechanism of aerodynamic interference in overlapping rotors of heavy-load electric vertical take-off and landing(eVTOL)aircraft,this paper aims to reveal the aerodynamic interference characteristics and flow field evolution laws of overlapping rotor configurations in hovering conditions through numerical simulation methods.The research method involves constructing a computational model for rotor flow fields and aerodynamic characteristics based on the Reynolds-averaged Navier-Stokes(RANS)equations and the Spalart-Allmaras(S-A)turbulence model.The dynamic simulation of rotor rotational motion was achieved by using the moving nested grid technology.The reliability of the computational method was ensured through the grid independence verification and the comparison with experimental data.The research results indicate that in overlapping rotor systems,rotorⅡexperiences a decrease in thrust,significant power fluctuations,and reduced hovering efficiency due to continuous interference from the adjacent rotor’s wake and blade-vortex interactions.Blade-tip vortices undergo breakage,fusion,and secondary rolling in the overlapping region,forming large-scale turbulent structures that lead to attenuation of the induced velocity field and aerodynamic efficiency losses.Additionally,the interaction between the rotor downwash and the fuselage triggers a“fountain effect”and a sudden increase in surface pressure on the fuselage,exacerbating flow field distortion.Based on the aforementioned mechanisms,the safe flight of overlapping rotor configurations can be achieved by optimizing the configuration strategy of the rotational speed phase difference between adjacent blades.This study provides a theoretical basis for the rotor layout design and the aerodynamic performance enhancement of heavy-load eVTOL aircraft.展开更多
文摘高超声速转捩研究飞行器(Hypersonic Transition Research Vehicle,HyTRV)是为研究高超声速复杂三维边界层转捩而设计的升力体标模,其外形更接近真实飞行器。为深入认识HyTRV边界层稳定性特征及转捩机制,验证数值模拟和理论分析结果,本文在马赫数6常规风洞中,采用红外热成像技术和高频压力传感器,获得了0°和2°攻角时HyTRV标模下表面(迎风面)的边界层转捩阵面及不稳定波的演化特征,并与一维稳定性分析结果进行了对比。研究结果表明:攻角为2°时,标模下表面的横流失稳区较0°攻角时范围缩小且位置后移,标模中心线处转捩早于两侧横流区。另外,横流区存在宽频的高频信号,信号幅值在转捩完成前达到饱和。该信号包含多频段扰动,多种扰动之间相互作用导致频谱变宽,最终促使边界层转捩变为湍流。
基金supported by the National Natural Science Foundation of China(No.11872211)。
文摘Focusing on the unclear mechanism of aerodynamic interference in overlapping rotors of heavy-load electric vertical take-off and landing(eVTOL)aircraft,this paper aims to reveal the aerodynamic interference characteristics and flow field evolution laws of overlapping rotor configurations in hovering conditions through numerical simulation methods.The research method involves constructing a computational model for rotor flow fields and aerodynamic characteristics based on the Reynolds-averaged Navier-Stokes(RANS)equations and the Spalart-Allmaras(S-A)turbulence model.The dynamic simulation of rotor rotational motion was achieved by using the moving nested grid technology.The reliability of the computational method was ensured through the grid independence verification and the comparison with experimental data.The research results indicate that in overlapping rotor systems,rotorⅡexperiences a decrease in thrust,significant power fluctuations,and reduced hovering efficiency due to continuous interference from the adjacent rotor’s wake and blade-vortex interactions.Blade-tip vortices undergo breakage,fusion,and secondary rolling in the overlapping region,forming large-scale turbulent structures that lead to attenuation of the induced velocity field and aerodynamic efficiency losses.Additionally,the interaction between the rotor downwash and the fuselage triggers a“fountain effect”and a sudden increase in surface pressure on the fuselage,exacerbating flow field distortion.Based on the aforementioned mechanisms,the safe flight of overlapping rotor configurations can be achieved by optimizing the configuration strategy of the rotational speed phase difference between adjacent blades.This study provides a theoretical basis for the rotor layout design and the aerodynamic performance enhancement of heavy-load eVTOL aircraft.
