Engineering calculation and analysis of aerodynamic heating for hypersonic rocket sled

Parallel Computation in Hypersonic Aerodynamic Heating Problem

A parallel computational fluid dynamics code has been developed for the study of aerodynamic heating problem in hypersonic flows. The code employs the 3D Navier-Stokes equations as the basic governing equations to simulate the laminar hypersonic flow. The cell centered finite volume method based on structured grid is applied for spatial discretization. The AUSMPW+ scheme is used for the invisci...

!calculating Aerodynamic Heating on Sounding Rocket Tangent Ogive Noses

A method is presented for calculating the aerodynamic heating and shear stresses at the wall for tangent ogive' noses that are slender enough to maintain an attached nose shock through that. portion of flight duringwhich heat transfer from' the botundary layer to the wall is significant. The lower entropy of the attached nose shock combined with the inclusion of the streamwise pressure gradient...

Thermo-viscopiastic Analysis of Hypersonic Structures Subjected to Severe Aerodynamic Heating

Critical Velocities for Rocket Sled Excitation of Rail Resonance

he rocket sled test facility at the Holloman Air Force Base in New Mexico provides a unique and valuable test venue for evaluating advanced missile technology at representative flight velocities. Recent failures at the facility underscore the inherent high-risk nature of supersonic sled tests and undermine their potential value to missile development programs. This article addresses one potenti...

Laminar and Turbulent Aero Heating Predictions over Blunt Body in Hypersonic Flow

In the present work, an engineering method is developed to predict laminar and turbulent heating-rate solutions for blunt reentry spacecraft at hypersonic conditions. The calculation of aerodynamic heating around blunt bodies requires alternative solution of inviscid flow field around the hypersonic bodies. In this paper, the procedure is of an inverse nature, that is, a shock wave is assumed a...