Accession Number : AD0833513
Title : STABILITY DERIVATIVES OF 10 DEGREES PITCHING CONE IN HYPERSONIC VISCOUS FLOW.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Fulkerson, Grover D.
Report Date : DEC 1967
Pagination or Media Count : 52
Abstract : Using momentum integrals, an expression for the boundary layer displacement thickness is obtained from the unsteady equations of motion on a sharp, right, circular cone oscillating about a small mean angle of attack in hypersonic flow. The effects of the boundary layer displacement on the stability derivatives for small pitching oscillations were considered for an insulated cone with a Prandtl number of 1. Numerical results for a 10 degrees half-angle cone indicate that the viseous contributions to the stability derivatives may be considerable for low Reynolds numbers at high Mach numbers. (Author)
Descriptors : *HYPERSONIC FLOW), (*CONICAL BODIES, BOUNDARY LAYER, THICKNESS, MOMENTS, VISCOSITY, ANGLE OF ATTACK, EQUATIONS OF MOTION, REYNOLDS NUMBER, PRESSURE, STABILITY, MACH NUMBER, THESES, OSCILLATION, PITCH(MOTION), PRANDTL NUMBER, HYPERSONIC CHARACTERISTICS, COMPRESSIBLE FLOW, NUMERICAL ANALYSIS.
Subject Categories : Numerical Mathematics
Distribution Statement : APPROVED FOR PUBLIC RELEASE