Accession Number : ADB029574
Title : The Three-Dimensional Shock and Pressure (3DSAP) Approximate Flow Field Technique. Volume I. Engineering Analysis.
Descriptive Note : Interim rept. Nov 76-May 77 on Task 2,
Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA RE-ENTRY SYSTEMS DEPT
Personal Author(s) : Hall, Darryl W.
Report Date : MAY 1977
Pagination or Media Count : 85
Abstract : An approximate flow field technique is developed for the prediction of inviscid aerodynamic characteristics of re-entry vehicles with asymmetric nose geometries at angle of attack and/or sideslip. The subsonic flow region on the nose is approximated using a correlation for surface pressures and iterating on the shock position to satisfy mass continuity. The axisymmetric frustum is computed using the exact three-dimensional inviscid equations, explicitly treating crossflow effects. (Author)
Descriptors : *FLOW FIELDS, *REENTRY VEHICLES, INVISCID FLOW, THREE DIMENSIONAL FLOW, NOSE TIPS, FRUSTUMS, EQUATIONS OF MOTION, AERODYNAMIC LOADING, SHOCK, PRESSURE, ANGLE OF ATTACK, SIDESLIP, TRANSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS.
Subject Categories : Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE