STATIC AERODYNAMIC CHARACTERISTICS AT MACH 5 AND 8 OF AN AERODYNAMICALLY CONTROLLABLE WINGED RE-ENTRY CONFIGURATION; PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS

Abstract

Six-component aerodynamic data were obtained at Mach 5 and 8 for a winged re-entry configuration having aerodynamic controls. The basic model consisted of a clipped delta wing with an over-slung body. The main controls tested were a deflected apex and partial-span trailing-edge flaps. Data were also obtained on the effect of tip fins, full-span trailing-edge flap, and trailing-edge spoiler. At Mach number 5 the data were obtained over an angle of attack range from -30 degrees to +45 degrees at a unit Reynolds number of 2.26 x 10 to the 6th power. At Mach number 8 the angle of attack range was -54 degrees to +54 degrees at the same unit Reynolds number.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1963
Accession Number
AD0608304

Entities

People

  • Lawrence Meckler

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Coordinate Systems
  • Experimental Data
  • Flow
  • Fluid Dynamics
  • Heat Transfer
  • Hypersonic Glide Vehicles
  • Hypersonic Wind Tunnels
  • Leading Edges
  • Photographs
  • Research Facilities
  • Shock Tunnels
  • Supersonic Wind Tunnels
  • Test And Evaluation
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow