Pressure Distributions on Some Delta Wings at M=4.

Abstract

Complete pressure distributions are presented for a series of delta wings tested through an incidence range at a Mach number of 4. The results have been integrated to obtain lift and drag coefficients and the values found are in good agreement with the trend from measurements on similar wings at lower Mach numbers. Some of the models were designed to test a possible method of engine/airframe integration. The results show that it is possible to add volume to the rear of the wing without increasing the drag of the forebody, thus confirming the proposed method of integration. (Author)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1980
Accession Number
ADA098688

Entities

People

  • K. C. Moore
  • L. C. Squire

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircrafts
  • Airframes
  • Aspect Ratio
  • Boundary Layer
  • Cylindrical Bodies
  • Delta Wings
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Thin Wings
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Mechanics and Fluid Dynamics.
  • Regression Analysis.