Accession Number:

ADA028981

Title:

Survey of Three-Dimensional Flow Fields in The Presence of Wings at M = 2.48.

Descriptive Note:

Final rept.,

Corporate Author:

DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT

Personal Author(s):

Report Date:

1976-07-01

Pagination or Media Count:

55.0

Abstract:

A survey investigation involving parametric models of the Generic Ordnance Ramjet Engine GORJE vehicle was conducted to obtain detailed information about the flow field behind movable wing control surfaces. The objective was to determine the effects of wing planform, thickness ratio, and deflection angle on total and static pressure and on local Mach number distributions at possible locations for inlet Installations. In all phases the free-stream wind tunnel conditions were identical at M 2.48 and at unit Reynolds number of about 3,050,000ft. The first phase involved a sting-mounted, 110-scale model. The survey indicated that an interdigitated inlet location is preferable on the basis of flow field total pressure recovery in both and x wing orientations for angles of attack to or - 4 deg and for wing deflections less than about or - 6 deg. The second phase, involving a wall-mounted model, revealed a complex flow field. There was interaction between the incipient conical body shock wave and the wing wake. This study provides a data base from which it is possible to select inlet locations with acceptable pressure recovery, although caution must be exercised to stay within the limitations of the measured parameters.

Subject Categories:

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

Distribution Statement:

APPROVED FOR PUBLIC RELEASE