Wind Tunnel Tests of Supersonic Lifting Bodies at Mach Number 1.5 to 4.0.

Abstract

Wind tunnel tests were conducted on four new wedge shaped configurations, one of which approached that of a wave rider design. Aerodynamic data are presented for Mach numbers 1.5 through 4.0 with angle of attack variation from -10 to +7 deg. The data are similar to previously reported results with the one exception being the near wave rider configuration. This configuration resulted in lift/drag data being invariant with respect to Mach number. The maximum value of lift/drag reached approximately 3.0. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1977
Accession Number
ADA037380

Entities

People

  • Charles J. Nietubicz

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Loading
  • Base Pressure
  • Coefficients
  • Drag
  • Engineering
  • Flow
  • Fluid Dynamics
  • Free Stream
  • Lifting Bodies
  • Mach Number
  • Reynolds Number
  • Shape
  • Stagnation Temperature
  • Test Facilities
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow