Accession Number : ADA190870
Title : Experimental Investigation of the Hypersonic Flow Over a Six Finned Configuration.
Descriptive Note : Final rept.,
Corporate Author : NEW YORK UNIV WESTBURY ANTONIO FERRI LABS
Personal Author(s) : Agnone, A M ; Zakkay, V ; Parmar, K S
PDF Url : ADA190870
Report Date : Jun 1987
Pagination or Media Count : 47
Abstract : Experimental data of the flow field over a six-finned configuration are compared with computations from an inviscid Euler and a parabolized Navier-Stokes (PNS) code to assess their accuracy. The experiments were conducted with a smooth and a grooved cylinder in a hypersonic (M=6.5) wind tunnel. Surface oil flow patterns, surface pressures, local heat flux rates and flow field pitot surveys are presented. The PNS computations are in good agreement with the measurements in the viscid regions. However, significant differences are noted in the viscous regions possibly due to nose tip bluntness effects and the associated entropy layer. Keywords: Hypersonic, Aerodynamics, Fluid mechanics, Navier Stokes, Code validation, Finned configuration, Experiment.
Descriptors : *FINS, *HYPERSONIC FLOW, *AERODYNAMIC CONFIGURATIONS, ACCURACY, AERODYNAMICS, BLUNT BODIES, CODING, COMPUTATIONS, CONFIGURATIONS, CYLINDRICAL BODIES, ENTROPY, EXPERIMENTAL DATA, FLOW FIELDS, FLUID MECHANICS, FLUX(RATE), GROOVING, HEAT FLUX, INVISCID FLOW, LAYERS, NAVIER STOKES EQUATIONS, NOSE TIPS, OILS, PARABOLAS, PATTERNS, PITOT TUBES, PRESSURE, REGIONS, SURFACE PROPERTIES, SURFACES, SURVEYS, VALIDATION, VISCOSITY, VISCOUS FLOW, WIND TUNNELS, GUIDED MISSILES
Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
Distribution Statement : APPROVED FOR PUBLIC RELEASE