Investigations of Three-Dimensional Shock/Shock Interactions over Symmetrical Intersecting Wedges

Xiang, Gaoming; Wang, C.; Teng, Honghui; Jiang, Zonglin

doi:10.2514/1.j054672

Cited by 15 publications

(4 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The dimension of the characteristic line direction is replaced by the time dimension. The detailed procedure of the "spatial dimension reduction" approach has been previously published [26][27][28] .…”

Section: Theoretical Approach and Numerical Methodsmentioning

confidence: 99%

Investigations on the complex flows induced by dual-swept/dual-ramp wedges in supersonic flows

Gao

Xiang

Tang

et al. 2020

Sci Rep

Self Cite

View full text Add to dashboard Cite

The caret inlet with a dual-swept/dual-ramp configuration has excellent stealth performance and aerodynamic capability. Most previous investigations on this configuration have focused on experiments and numerical simulations but there are relatively few theoretical investigations. In this study, the flow field characteristics of dual-swept/dual-ramp configuration are investigated analytically and numerically. An analytical approach that combines the shock dynamics with a "spatial dimension reduction" was used to analyze the characteristics of the wave structures and state parameters of the flow field. The effects of the sweep angles and inflow Mach number on the flow field characteristics are investigated. The results indicate that the problem of shock/shock interaction in two intersecting wedges of large back-swept angle is a problem of weak shock interaction. Therefore, the theory of weak shock interaction is used to investigate the flow field characteristics, including the uniformity of the flow field and the total pressure recovery performance.

show abstract

Section: Theoretical Approach and Numerical Methodsmentioning

confidence: 99%

Investigations on the complex flows induced by dual-swept/dual-ramp wedges in supersonic flows

Gao

Xiang

Tang

et al. 2020

Sci Rep

Self Cite

View full text Add to dashboard Cite

show abstract

“…A low-cost and highly efficient way to analyse the evolution of the 3-D steady shock wave is using the method of spatial dimension reduction (Yang et al 2012;Xiang et al 2016) because the theory of two-dimensional (2-D) shock waves is well developed. To make the spatial dimension reduction available, the hypersonic equivalence principle (Anderson 2019;Wang 2019) connecting the steady flow with the unsteady flow in one fewer space dimension can be adopted to equivalently transform the 3-D steady ICS into a 2-D moving shock with an initial elliptical shape.…”

Section: Introductionmentioning

confidence: 99%

Kinks on elliptical convergent shock waves in hypersonic flow

Si,

2023

J. Fluid Mech.

View full text Add to dashboard Cite

Kinks commonly appear on the convergent shock surface when an internal conical flow deviates from the axisymmetric state. In this paper, the formation mechanisms of kinks on internal conical shocks (ICSs) generated by elliptical ring wedges with typical entry aspect ratios ( $AR{\rm s}$ ) in a Mach 6 flow are revealed using a theoretical method, in which the spatial evolution of the three-dimensional elliptical ICS is converted into a temporal evolution of a two-dimensional elliptical moving shock (EMS) using the hypersonic equivalence principle. To simultaneously track the shock front of the EMS and the disturbances propagating along it, a front-disturbance tracking method (FDTM) based on geometrical shock dynamics is proposed. It is found that the shock–compression disturbances from the same family initially near the major axis catch up with the disturbance initially emitted from the major axis to form kinks on the EMS. The equivalent kink formation positions predicted by the FDTM always lag behind the real kink formation positions on the elliptical ICS because the applicability of the hypersonic equivalence principle decays as the shock strengthens along the incoming flow direction. The accuracy of the equivalent kink formation positions predicted by the FDTM gradually declines with the reduction in $AR$ , but it can be significantly improved for all $AR{\rm s}$ after a modification of the equivalent relationship using the shock angle in the major plane of the elliptical ICS, which provides a new way to solve the kinks on the elliptical ICS.

show abstract

“…The earlier studies conducted parametric studies by varying the major geometrical parameters such as cone angle or cowl leading-edge radius to get the desirable performance (Chen et al 2005a, b;Zha et al 1997). Hypersonic inlets have also been analyzed in the recent past (Chang et al 2009;Liang et al 2008;Nair et al 2005;Xiang et al 2020a) The analysis of 3D inlets with sidewall compression (Xiang et al 2020b) and the investigation of 3D shock interactions over wedges (Xiang et al 2021;Xiang et al 2016) provided a detailed study on the shock interaction problems in the intake flow field. A detailed aerodynamic analysis was conducted by Nair et al (Nair et al 2005) using Reynoldsaveraged Navier-Stokes to compute the flow through a hypersonic inlet.…”

Section: Introductionmentioning

confidence: 99%

Flow Characteristics of a Mixed Compression Hypersonic Intake

2022

JAFM

View full text Add to dashboard Cite

The flow field in a two-dimensional hypersonic mixed-compression inlet in a freestream Mach numbers of M∞ =2.0, 3.0, and 5.0 are numerically solved to understand the effect of throat area variation. The exit area ratio variation is simulated by placing a plug insert at different axial locations at the exit of the model. The flow field is achieved computationally by solving the Reynolds Averaged Navier-Stokes equations in a finite volume framework. For each flow condition, the variation in shock structure is analyzed and the variation of the oblique shock wave angle with the mass flow rate is calculated theoretically and compared with the present CFD analysis. The variation in oblique shock angle is calculated in terms of the mass flow rate by considering the capture area and spillage flow through the inlet. The theoretical results suggest that the method can predict the inlet operating conditions at different freestream Mach numbers and area ratios. This method can quantify the reduction in mass flow rate due to the throttling effect by analyzing the flow field shock pattern. The effects of various important performance parameters such as free stream Mach number, total pressure recovery, and mass flow ratio were then numerically investigated. As the Mach number is increased, the total pressure recovery is reduced, but the maximum value of the mass flow rate is increased. The analysis is also focused on the effect of throat area variation on performance parameters at each Mach number. The characteristic curve of the inlet is then obtained for each free stream Mach number.

show abstract

Investigations of Three-Dimensional Shock/Shock Interactions over Symmetrical Intersecting Wedges

Cited by 15 publications

References 15 publications

Investigations on the complex flows induced by dual-swept/dual-ramp wedges in supersonic flows

Investigations on the complex flows induced by dual-swept/dual-ramp wedges in supersonic flows

Kinks on elliptical convergent shock waves in hypersonic flow

Flow Characteristics of a Mixed Compression Hypersonic Intake

Contact Info

Product

Resources

About