Launch-vehicle simulations using a concurrent, implicit Navier-Stokes solver

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Abstract
A large-scale multibody launch-vehicle simulation at supersonic speed is described. The simulation was conducted on a 256-node Intel Delta machine using a concurrent implementation of the Aerospace Launch System Implicit/Explicit Navier-Stokes code. This general Navier-Stokes solver has been used for a broad range of practical simulations. Those of interest involve a variety of nozzle flows and multibody launch-vehicle configurations such as the Titan IV. The code utilizes a finite volume total-variation-diminishing scheme for computing both steady and unsteady solutions to the three-dimensional compressible Navier-Stokes equations. The scheme is second-order accurate in space and is fully vectorized for operation on Cray computers. A line-by-line relaxation algorithm is used to accelerate the convergence for steady-state solutions. The code employs a variety of features that increase its practical utility. These include multibody configurations, turbulence modeling, and propellant-burning capabilities. The procedures for extending this code to distributed-memory parallel computers are described. Results of the application to a Titan IV launch vehicle at freestream Mach number 1.6 are discussed.

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