NASA NTRS · 19910036793
Numerical simulation of fluid flow around a scramaccelerator projectile
Abstract
Numerical simulations of the fluid motion and temperature distribution around a 'scramaccelerator' projectile are obtained for Mach numbers in the 5-10 range. A finite element method is used to solve the equations of motion for inviscid and viscous two-dimensional or axisymmetric compressible flow. The time-dependent equations are solved explicitly, using bilinear isoparametric quadrilateral elements, mass lumping, and a shock-capturing Petrov-Galerkin formulation. Computed results indicate that maintaining on-design performance for controlling and stabilizing oblique detonation waves is critically dependent on projectile shape and Mach number.
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Pepper, Darrell W., Humphrey, Joseph W., Sobota, Thomas H.. 1991-01-01. Numerical simulation of fluid flow around a scramaccelerator projectile. https://ntrs.nasa.gov/citations/19910036793
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