WIND TUNNEL INVESTIGATION OF FAVORABLE INTERFERENCE TO INCREASE LIFT-DRAG RATIOS OF SUPERSONIC AIRCRAFT. PART I - PRESSURE FIELDS AROUND A BODY AND AN INLET.

Abstract

Wind-Tunnel tests at a Mach number of 2.87 were to measure the intensity and spatial distribution of low-pressure fields that radiate back from an indented side portion of a body and the high-pressure fields that radiate from the external wedge sides of an engine air inlet. The measured pressure distributions were integrated over a proposed thin flat-plate wing proposed for separating the body and inlet fields. The resulting favorable increase in normal-force coefficient was as much as 0.035 at zero angle of attack and corresponds to about 15 percent of the cruise lift required for an attack aircraft. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1964
Accession Number
AD0601232

Entities

People

  • Ernie W. Pope
  • Richard M. Hartley

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Attack Aircraft
  • Fighter Aircraft
  • High Pressure
  • Mach Number
  • Pressure Distribution
  • Spatial Distribution
  • Supersonic Aircraft
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Plasma Physics / Magnetohydrodynamics

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow