Numerical Computation of Hypersonic Laminar Near-Wake Flow via Navier-Stokes Solver,

Abstract

Numerical solutions of the Navier-Stokes equations are obtained for laminar hypersonic near-wake flow behind cones at zero angle of attack. Numerical simulations are presented for a cone with a 7-degree half-angle. The study includes three values of free-stream mach number (4.32, 6.32, 10.0) and four values of Reynolds number ranging from 21500 to 172000 referenced to base diameter. The numerical scheme is patterned after the Alternating Direction Implicit method of Beam and Warming, with modification to include finite-volume discretization and spatially variable time step for accelerating convergence to steady state. Comparisons are made with experimental data for base pressure, length of the recirculating region, and general flow-field structure. Effects of Mach and Reynolds numbers on the laminar near-wake flowfield structure are reported.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1985
Accession Number
ADA161021

Entities

People

  • Raul J. Conti
  • Yehuda Tassa

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Base Pressure
  • Boundary Layer
  • Computational Fluid Dynamics
  • Experimental Data
  • Fluid Dynamics
  • Free Stream
  • Layers
  • Mach Number
  • Measurement
  • Navier Stokes Equations
  • Pressure Distribution
  • Reynolds Number
  • Stagnation Point
  • Static Pressure
  • Steady State
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers