Accession Number:

ADA018157

Title:

Flow-Field Study about a Hemisphere-Cylinder in the Transonic and Low Supersonic Mach Number Range

Descriptive Note:

Final rept. 1 Sep 1973-30 Sep 1974

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1975-11-01

Pagination or Media Count:

59.0

Abstract:

A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range M 0.7 to 2.0. For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE