A Program for Computing Steady Inviscid Three-Dimensional Supersonic Flow on Reentry Vehicles. Volume I: Analysis and Programming
Abstract
A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a FORTRAN computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. In this report the analytical and numerical development of the procedure is presented and the associated computer code is described. A comparison report contains detailed instructions for operating the code and interpreting the output results.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 11, 1977
- Accession Number
- ADA040833
Entities
People
- A. B. Wardlaw Jr.
- J. B. Bell
- J. M. Solomon
- M. Ciment
- R. E. Ferguson
Organizations
- Naval Ordnance Laboratory