Double Wedge Shockwave Interaction Flow Characterization

International Journal of Heat and Mass Transfer, 2014

Shock wave boundary layer interaction phenomena play a critical role in the design of supersonic and hypersonic vehicles. Consequently, this paper mainly focuses on hypersonic flow over a double wedge

Shock Waves, 2008

In this paper, the shock pattern oscillations induced by shock/shock interactions over double-wedge geometries in hypersonic flows were studied numerically by solving 2D inviscid Euler equations for a multi-species system. Laminar viscous effects were considered in some cases. Temperature-dependent thermodynamic properties were employed in the state and energy equations for consideration of the distinct change of the thermodynamic state. It was shown that the oscillation results in high-frequency fluctuations of heating and pressure loads over wedge surfaces. In a case with a relatively lower free-stream Mach number, the shock/shock interaction structure maintains a seven-shock configuration during the entire oscillation process. On the other hand, the oscillation is accompanied by a transition between a six-shock configuration (regular interaction) and a seven-shock configuration (Mach interaction) in a case with a higher free-stream Mach number. Numerical results also indicate that the critical wedge angle for the transition from a steady to an oscillation solution is higher compared to the corresponding value in earlier numerical research in which the perfect diatomic gas model was used.

THE 8TH ANNUAL INTERNATIONAL SEMINAR ON TRENDS IN SCIENCE AND SCIENCE EDUCATION (AISTSSE) 2021

In the design of hypersonic and supersonic vehicles, the critical challenge will be the phenomenon of shock wave interactions. It becomes increasingly important because the aerodynamic heating and pressure loads raises so greatly that the performance of the flight and the basic structure are going to be largely affected. In the present paper we performed a numerical model of the problem and analyzed using a commercial Computational Fluid dynamics software, and compared the results with the published data. The key element that we have considered is the double wedge problem and studied the characteristics of the aerodynamics using CFD. The conditions of type III and IV interactions are studied. Our analysis successfully characterized the shock wave interactions. Almost very similar conclusions were made by the published results. There has been a zone of the shockwave interaction and the intersection of this zone has been shared with the intersection of second shockwave due to the second wedge. The slip lines are not observed as the inconsistency.

Journal of Physics: Conference Series, 2019

Present investigations are focused on the study of effects of dimensional and parametric changes in shock wave boundary layer interaction (SWBLI) for an axisymmetric double wedge with leading edge bluntness in hypersonic flows. This study is specifically the point of interest since it attributes most of the characteristics of the hypersonic flow around the atmosphere re-entry vehicles. Successfully implemented simulations in hypersonic flow are in a double wedge configuration, to study shock wave boundary layer interaction in hypersonic flows. Inversion radius was found at different deflection angles for change in leading edge radius (LER). It was found that for lower deflection angle Crocco’s theorem affect the flow early compared to higher deflection angles. Shock-shock Interaction-I (SSI I) and Shock-shock Interaction-II (SSI II) shifts downstream with increase in leading edge radius. (Key Words: Hypersonic flows, Shock wave boundary layer interaction, Shock–shock interaction and...

Shock Waves, 2009

Acta Astronautica, 2018

Hypersonic shock wave transitional boundary layer interactions can result in significantly greater peak surface heat transfer than laminar or turbulent interactions. Consequently, the understanding of the flowfield structure of hypersonic shock wave transitional boundary layer interactions is important. Moreover, the capability to predict the mean and fluctuating aerothermodynamic loading due to such interactions is needed for effective design of hypersonic vehicles. A review of hypersonic shock wave transitional boundary layer interaction research since 1993 is presented. Significant progress has been achieved in the understanding of the flowfield structure. The most promising prediction methodology is Direct Numerical Simulation (DNS); however, DNS requires dynamic (i.e., time varying) inflow boundary conditions for five flow variables (i.e., three components of velocity, and two thermodynamic variables), and such experimental data is presently infeasible. Additional research is needed to understand the effect of assumed dynamic inflow boundary conditions on DNS prediction of aerothermodynamic loads.

Advances in Aerodynamics, 2020

Despite over fifty years of research on shock wave boundary layer effects and interactions, many related technical issues continue to be controversial and debated. The present survey provides an overview of the present state of knowledge on such effects and interactions, including discussions of: (i) general features of shock wave interactions, (ii) test section configurations for investigation of shock wave boundary layer interactions, (iii) origins and sources of unsteadiness associated with the interaction region, (iv) interactions which included thermal transport and convective heat transfer, and (v) shock wave interaction control investigations. Of particular interest are origins and sources of low-frequency, large-scale shock wave unsteadiness, flow physics of shock wave boundary layer interactions, and overall structure of different types of interactions. Information is also provided in regard to shock wave investigations, where heat transfer and thermal transport were important. Also considered are investigations of shock wave interaction control strategies, which overall, indicate that no single shock wave control strategy is available, which may be successfully applied to different shock wave arrangements, over a wide range of Mach numbers. Overall, the survey highlights the need for additional understanding of fundamental transport mechanisms, as related to shock waves, which are applicable to turbomachinery, aerospace, and aeronautical academic disciplines.

43rd Fluid Dynamics Conference, 2013

Aerospace Science and Technology, 2009

This article is devoted to the experimental works carried out in the R2Ch blow-down wind tunnel in the framework of the atmospheric re-entry PRE-X demonstrator program and to the fundamental studies performed on a hollow cylinder-flare relative to crucial problem of the transitional shock-wave/boundarylayer interaction. Shock-wave/boundary-layer interactions in hypersonic flows may have major consequences on thermal loads, especially if the shock is strong enough to induce separation. The heat-flux density levels in the interaction region strongly depend on the nature, laminar or turbulent of the boundary-layer. Special attention should be paid to transitional interactions, which are likely to exist at altitude where the Mach number is high and the density low. The wide Reynolds number range achievable in the R2Ch facility and reliable heat-flux measurements by infrared thermography have allowed to investigate the viscous interaction on the deflected flaps of the demonstrator model and to point out the laminar-to-turbulent boundary-layer natural and forced transition, in the light of the in-depth analysis of results obtained from the hollow cylinder-flare study.

Journal of Visualization, 2004