Accession Number : ADA304886
Title : Numerical Investigation of Subsonic Flow Over Bodies of Revolution and a Typical Missile Forebody.
Descriptive Note : Master's thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Marvin, Ronald E.
PDF Url : ADA304886
Report Date : SEP 1995
Pagination or Media Count : 128
Abstract : It was the objective of this investigation to study the subsonic flow over a missile forebody. To this end, the NASA Ames developed OVERFLOW, three dimensional, Navier-Stokes Code was applied and detailed results were obtained for the missile forebody. The flow conditions were set at a Mach Number of 0.3 and Reynolds Number of two million for each angle of attack at 0, 2, 6, 10, and 14 degrees. These viscous flow solutions were compared with three inviscid flow solutions, namely Slender Body Theory, von Karman's Method, and the NASA Ames Panel Code called PMARC. As expected, the OVERFLOW and PMARC solutions were in good agreement at zero and small angles of attack. As the angle of attack was increased, the OVERFLOW solution showed the development of the vortical flow separation on the leeward side of the body. (AN)
Descriptors : *COMPUTATIONAL FLUID DYNAMICS, *SUBSONIC FLOW, *GUIDED MISSILE COMPONENTS, AERODYNAMIC CONFIGURATIONS, MATHEMATICAL MODELS, SLENDER BODIES, THESES, VORTICES, ANGLE OF ATTACK, THREE DIMENSIONAL, FLOW FIELDS, APPROXIMATION(MATHEMATICS), ERROR ANALYSIS, AERODYNAMIC FORCES, WAKE, HYDRODYNAMIC CODES, MACH NUMBER, NAVIER STOKES EQUATIONS, INVISCID FLOW, VISCOUS FLOW, FLOW SEPARATION, PRESSURE DISTRIBUTION, REYNOLDS NUMBER, INCOMPRESSIBLE FLOW, POTENTIAL FLOW, GUIDED MISSILE MODELS, LAPLACE TRANSFORMATION, BODIES OF REVOLUTION, POTENTIAL THEORY, LIFTING SURFACES.
Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
Distribution Statement : APPROVED FOR PUBLIC RELEASE