In the Martian atmosphere heavy storms occur, which transport dust particles even into the higher atmosphere, i.e. up to 40 km of altitude. These particles, with sizes of up to 20μm, consist of silicon oxides and iron oxides may affect the heat load on the heat shield during atmospheric entry. In this present study, these additional loads due to impingement of solid particles in hypersonic entr...

This report has been produced in order to address aerodynamic characteristics and stability and control issues relating to hypersonic vehicles that are deemed to be significantly different from those of the conventional (subsonic or supersonic) air vehicles. In particular we have addressed issues that are relevant to stability and control of hypersonic vehicles. This report should add to the ex...

The combination of multiplemodules in parallel manner is an important way to achieve the much higher thrust of scramjet engine. For the multiple-modules scramjet engine, when inlet unstarted oscillatory flow appears in a single-module engine due to high backpressure, how to interact with each module by massflow spillage, and whether inlet unstart occurs in other modules are important issues. Th...

Chemically reacting flows are common in engineering, such as hypersonic flow, combustion, explosions, manufacturing processes and environmental assessments. For the number of reactions can be significant (over 100) due to very large CPU requirements chemical 99%) a flow combustion problems presently beyond capabilities even largest supercomputers.Motivated by this, novel Deep Neural Networks (D...

The simulation of hypersonic flows presents some difficulties due to the interaction between boundary layers and shock waves and to the high total enthalpy. In order to achieve more accurate numerical results with respect to physics, a Reynolds stress model (RSM) has been implemented in the well validated Reynolds averaged Navier-Stokes solver QUADFLOW. The RSM developed and tested by Eisfeld, ...

This paper is devoted to predict laminar and turbulent heating rates around blunt re-entry spacecraft at hypersonic conditions. Heating calculation of a hypersonic body is normally performed during the critical part of its flight trajectory. The procedure is of an inverse method, where a shock wave is assumed, and the body shape that supports this shock, as well as the flowfield between the sho...

The accurate prediction of hypersonic flows is a key challenge for the design reentry bodies or aircraft. Knowledge concerning wall-bounded turbulence especially needed. present work fundamental study turbulent spatially developing flat-plate boundary layer subjected to high-enthalpy effects. influence air chemical reactions, typical high-speed regimes, investigated by means direct numerical si...