Accession Number : ADA111794

Title :   Comparison of Numerical Results and Measured Data for Smooth and Indented Nosetips,

Corporate Author : NAVAL SURFACE WEAPONS CENTER SILVER SPRING MD

Personal Author(s) : Hsieh,Tsuying

PDF Url : ADA111794

Report Date : 14 May 1981

Pagination or Media Count : 12

Abstract : Numerical calculations, using an unsteady implicit numerical algorithm which solves either the inviscid or the thin-layer Navier-Stokes equations, were performed for smooth and severely indented nosetips at hypersonic speed and zero angle of attack. The computed results of inviscid and laminar flowfield are compared to wind tunnel measured data for surface pressure, shock location, heat transfer and density distribution in the shock layer. Good agreements between the calculated and measured flowfield are obtained for smooth nosetip without flow separation. Difficulties in the simulation of severely indented nosetips with large separation bubble or sharp corner are discussed. (Author)

Descriptors :   *Nose tips, *Hypersonic flow, Navier Stokes equations, Approximation(Mathematics), Surface roughness, Numerical analysis, Algorithms, Comparison, Experimental data, Sharpness, Flow fields, Inviscid flow, Laminar flow, Concave bodies, Heat transfer, Shock, Layers, Reentry vehicles

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE