Energy deposition for flow and flight control has received significant interest in the past several decades due to its potential application to high-speed flow and flight control. This paper reviews recent progress and recommends future research.

The numerical investigation of the interaction of an off-axis laser discharge in front of an ogive cylinder at Mach 3.4 is presented. Details of the physics of the interaction of the blast wave and heated region with the ogive cylinder shock structure and the effect of this interaction on the drag, side force and pitching moment are included. The location of laser discharge and the amount of energy added to the gas by the laser are two main factors affecting the flow. Increasing the energy absorbed by the gas increases the drag reduction, the desired side force and pitching moment. Increasing the distance of the discharge from the axis reduces both drag reduction and side force achieved by the laser discharge.

The recent revival of interest in developing new hypersonic vehicles brings attention to the need for accurate prediction of hypersonic flows by computational methods. One of the challenges is prediction of aerothermodynamic loading over the surface of the vehicles. Reynolds Average Navier-Stokes (RANS) methods have not shown consistent accuracy in prediction of such flows. Therefore, new methods including Large Eddy Simulations (LES) should be investigated. In this paper, the LES method is used for prediction of the boundary layer over a flat plate. A new recycling-rescaling method is tested. The method uses total enthalpy and static pressure along with the velocity components to produce the best results for the Law of the Wall, turbulent statistics and turbulent Prandtl number.

View Video Presentation: https://doi.org/10.2514/6.2021-2882.vid There is a recent reinterest in hypersonic flight with special attention on the capability of numerical simulations. Reynolds-Averaged Navier-Stokes (RANS) calculations showed that RANS is incapable of predicting complicated hypersonic flows such as shock wave boundary layer interaction accurately. In this paper, we use Large Eddy Simulation (LES) for the prediction of a cold wall hypersonic turbulent flow over a flat plate. The sensitivity of the model relative to the inflow wall temperature, recycling method, and the number of cells in the boundary layer will be presented. This is a preparation step for using LES to predict aerothermodynamic loading for more complicated hypersonic turbulent flows.