WIND-TUNNEL INVESTIGATION OF FAVORABLE INTERFERENCE TO INCREASE LIFT-DRAG RATIOS OF SUPERSONIC AIRCRAFT: PART II: AN OPTIMIZED WING-BODY-INLET CONFIGURATION.

Abstract

The results of wind-tunnel tests conducted at a Mach number of 2.87 to investigate favorable interference effects on wing-body-inlet configurations are presented. The engine air inlet location and the body indentation angle for maximum lift increments were determined. These favorable lift increments correspond to about 20 percent of the cruise lift required for an attack aircraft. A fence, attached to the wing to reflect the shock wave emanating from the engine air inlet and to intensify the pressure field, increased the inboard lift but not sufficiently to overcome the resulting loss in lift ffrom the outboard section of the wing. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1964
Accession Number
AD0604731

Entities

People

  • David W. Moxley Jr.
  • Norman G. Ziegler
  • Richard M. Hartley

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Attack Aircraft
  • Fighter Aircraft
  • Inboard
  • Mach Number
  • Military Aircraft
  • Outboard
  • Shock
  • Shock Waves
  • Supersonic Aircraft
  • Vehicles
  • Waves
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Electromagnetic Wave Scattering and Antenna Radiation Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow