Accession Number:

ADA164155

Title:

Numerical Flow Field Calculations for a Missile Configuration at M = .6.

Descriptive Note:

Final rept.,

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1986-01-01

Pagination or Media Count:

48.0

Abstract:

Large separated flow region can seriously degrade the effectiveness of fins or any other control surface located in that region. A knowledge of the expected flow field can thus be very important in the initial design phase of a missile or projectile. The Aerodynamics Technology Branch of the US Army Missile Laboratory has requested numerical flow field data for a new missile design. Numerical computations have been made for the requested missile configuration at M 0.6 and the results of these computations are presented in this report. A thin-layer Navier-Stokes base flow code has been used to compute the flow field for a full missile configuration including the base region. Numerical calculations have been made for both laminar and turbulent flow conditions. Details of the computed flow field are presented in the form of plots showing surface pressure distribution, velocity vectors, stream function and Mach number contours, particle paths and boundary layer parameters. Author

Subject Categories:

  • Numerical Mathematics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE