Airbreathing hypersonic systems offer distinct performance advantages over rocket-based systems for space access vehicles. However, these performance advantages are dependent upon advances in current state-of-the-art technologies in many areas such as ram/scramjet propulsion integration, high temperature materials, aero-elastic structures, thermal protection systems, transition to hypersonics a...

Lockheed Martin Skunk Works, under a cooperative agreement with NASA, will build and fly the X-33, a half-scale prototype of a rocket-based, single-stage-to-orbit (S S T O) , reusable launch vehicle (RLV). A 0.007-scale model of the X-33 604B0002G configuration was tested in four hypersonic facilities at the NASA Langley Research Center to examine vehicle stability and control characteristics a...

For the last quarter of 20th century, Concorde airliners and other supersonic aircraft shuttled wealthy passengers between North America Europe at speeds up to 600 m/s (about 1350 mph). The planes were retired in 2003. They had grown prohibitively expensive worried passengers, who couldn’t help but notice that planes’ windows too hot touch.Today, however, several airlines have plans reinstate j...

Airbreathing hypersonic systems offer distinct performance advantages over rocket-based systems for space access vehicles. However, these performance advantages are dependent upon advances in current state-of-the-art technologies in many areas such as ram/scramjet propulsion integration, high temperature materials, aero-elastic structures, thermal protection systems, transition to hypersonics a...

Numerical results are presented for the shock-boundary layer interactions in a hypersonic flow over a sharp leading edge compression corner. In this study, a second- order Godunov type scheme based on solving a Generalized Riemann Problem (GRP) at each cell interface is used to solve thin shear layer approximation of laminar Navier-Stokes (N-S) equations. The calculated flow-field shows general...

Abstract. The Direct Simulation Monte-Carlo (DSMC) technique is used for numerical analysis of rarefied-gas hypersonic flows near a blunt plate, wedge, two side-by-side plates, disk, torus, and rotating cylinder. The role of various similarity parameters (Knudsen and Mach numbers, geometrical and temperature factors, specific heat ratios, and others) in aerodynamics of the probes is studied. Im...

A validation study is presented for a numerical code which calculates a two-dimensional steady-state solution for inviscid hypersonic flows in the presence of strong surface blowing. A higher-orde: Godunov-type finite-volume approach is used to discretize the inviscid Euler equations. Interface values of the state quantities are reconstructed nsing a monotone interpolation technique suggested b...