Accession Number:

ADA218749

Title:

Comparison of Navier-Stokes Computation and Experiment for Pointed, Spherical, and Flat Tipped Shell at Mach 2.95

Descriptive Note:

Technical rept.

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Report Date:

1990-01-01

Pagination or Media Count:

60.0

Abstract:

A computational fluid dynamics study is described and results are shown for a tangent ogive-cylinder model with pointed, spherical, and flat nosetips at Mach number 2.95. The flow conditions simulate wind tunnel tests conducted at Princeton University Gas Dynamics Laboratory. The primary objective is to compare the computational and experimental results and assess the accuracy of computational approach. Two thin-layer Navier-Stokes computational techniques are used in conjunction to compute the flow fields of interest. The first method computes the flow in the vicinity of the blunt nosetip and provides inflow conditions for the second method, which computes the flow over the remainder of the body, excluding the base region. An empirical boundary layer transition model is implemented to partially account for the experimentally observed transition. Comparisons are made of surface pressure, turbulent boundary layer velocity profiles, skin friction coefficient, and of the nosetip flow structure. jhd

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE