Flowfield computation of entry vehicles
Abstract
The equations governing the multidimensional flow of a reacting mixture of thermally perfect gasses were derived. The modeling procedures for the various terms of the conservation laws are discussed. A numerical algorithm, based on the finitevolume approach, to solve these conservation equations was developed. The advantages and disadvantages of the present numerical scheme are discussed from the point of view of accuracy, computer time, and memory requirements. A simple onedimensional model problem was solved to prove the feasibility and accuracy of the algorithm. A computer code implementing the above algorithm was developed and is presently being applied to simple geometries and conditions. Once the code is completely debugged and validated, it will be used to compute the complete unsteady flow field around the Aeroassist Flight Experiment (AFE) body.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 1990
 Bibcode:
 1990STIN...9027986P
 Keywords:

 Aeroassist;
 Aerospace Vehicles;
 Computational Fluid Dynamics;
 Computer Programs;
 Conservation Equations;
 Conservation Laws;
 Flow Distribution;
 Mathematical Models;
 Algorithms;
 Computerized Simulation;
 Finite Volume Method;
 Memory (Computers);
 Unsteady Flow;
 Fluid Mechanics and Heat Transfer