Transverse jet in supersonic crossflows

Recent advances in cavity-based scramjet engine- a brief review

Research progress on strut-equipped supersonic combustors for scramjet application

Supersonic mixing in airbreathing propulsion systems for hypersonic flights

Hydrogen fuel in scramjet engines - A brief review

Thermochemical exploration of hydrogen combustion in generic scramjet combustor

Computational-fluid-dynamics-based design and analysis is presented for a full-scale scramjet combustor with kerosene fuel injected from struts placed in the combustor flowpath. Three-dimensional Navier-Stokes equations are solved with a K-e turbulence model using commercial computational-fluid-dynamics software. Combustion is modeled based on infinitely fast chemical kinetics. Lagrangian dispersed-phase analysis is considered for fueldroplet evaporation and mixing in the supersonic stream. Parametric studies are carried out to investigate the effect of combustor-inlet Mach number and total pressure on the flow development process. A higher combustor-entry Mach number and distributed-fuel-injection system will ensure the existence of predominant supersonic flow in the combustor. Simulations are also carried out to investigate two different kinds of fuel injection struts in the scramjet combustor performance. A distributed-fuel -injection system, required to avoid thermal choking, increases the three-dimensionality of the flowfield.

Liquid-Fueled Strut-Based Scramjet Combustor Design: A Computational Fluid Dynamics Approach

Optimization of a flight-worthy scramjet combustor through CFD

Numerical exploration of mixing and combustion in ethylene fueled scramjet combustor

Conjugate heat transfer studies are presented for high speed aerospace vehicle using commercial CFD software. Navier Stokes equations in the fluid domain and transient heat conduction equations in the solid domain are solved simultaneously to obtain the skin temperature history and other flow parameters. The computational methodology is applied to predict the surface temperature of high speed aerospace vehicle after validating the methodology against experimental results. Validation cases include laminar flow past axisymmetric double cone at Mach 4.57 and turbulent flow past circular cylinder at Mach 6.7. Computed flow field including cold wall heat flux, surface temperature distribution, surface temperature history match nicely with experimental as well as other numerical results. Temperature dependent material properties are found to have significant effect on the surface temperature prediction. Computed surface temperature of a high speed aerospace vehicle show good overall match with flight measured v...

Conjugate heat transfer analysis in high speed flows

P. Manna

Papers

Thermochemical exploration of hydrogen combustion in generic scramjet combustor

Liquid-Fueled Strut-Based Scramjet Combustor Design: A Computational Fluid Dynamics Approach

Optimization of a flight-worthy scramjet combustor through CFD

Numerical exploration of mixing and combustion in ethylene fueled scramjet combustor

Conjugate heat transfer analysis in high speed flows