Accession Number:

ADA224354

Title:

Supersonic/Hypersonic Aerodynamics and Heat Transfer for Projectile Design Using Viscous-Inviscid Interaction

Descriptive Note:

Final rept. May 1989-May 1990

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1990-06-01

Pagination or Media Count:

72.0

Abstract:

An aerodynamic design code for axisymmetric projectiles has been developed using a viscous-inviscid interaction scheme. Separate solution procedures for inviscid Euler and viscous boundary layer flowfields are coupled by an iterative solution procedure. This code yields body surface flow profiles in less than one minute of run time on minicomputers. These surface profiles represent converged solutions to both the inviscid and viscous equations. the capability of computing local reverse flow regions is included. The procedure is formulated for supersonic and hypersonic Mach numbers including both laminar and turbulent flow. In addition, aerodynamic heating equations are used to compute heat transfer coefficient and local Stanton number from flow profiles. Computed surface pressure profiles for Mach numbers 2 thru 6 are compared to wind tunnel measurements on cone-cylinder-flare projectiles. Computed surface heat transfer coefficients are compared to results obtained from wind tunnel measurements on cone-cylinder-flare, flat plate, and blunt-cone models at Mach numbers 5 and 10. Keywords Hypersonic flow Computational aerodynamics Boundary layers Heat transfer Projectile design.

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces

Distribution Statement:

APPROVED FOR PUBLIC RELEASE