PRELIMINARY DESIGN AND EXPERIMENTAL INVESTIGATION OF THE FDL-5A UNMANNED HIGH L/D SPACECRAFT. PART I. SUMMARY

Abstract

Conceptual design and experimental wind tunnel testing of unmanned entry research vehicles having high hypersonic lift/drag ratio and high volume are described. Analytic parametric data are presented for two lifting body classes designated HLD-35 and FDL-5. The FDL-5 is a unique configuration which is aerodynamically stabilized without outboard fins. Experimental aerodynamic and heat transfer fata from the Arnold Engineering Development Center Wind Tunnels A, B, C, and F are compared with analytic data for the FDL-5. Candidate structure and subsystems are selected for performing unmanned hypersonic research with the vehicle. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1968
Accession Number
AD0390193

Entities

People

  • J. T. Lloyd

Organizations

  • Lockheed Martin

Tags

Communities of Interest

  • Air Platforms
  • Autonomy
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Boundary Layer
  • Commerce
  • Control Systems
  • Geometry
  • Government (Foreign)
  • Governments
  • Heat Transfer
  • Landing Gear
  • Lifting Bodies
  • Nose Wheels
  • Parametric Analysis
  • Rocket Engines
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Software Engineering
  • Unmanned Aerial System (UAS) Autonomous Capabilities and Mission Reconnaissance.

Technology Areas

  • Autonomy
  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers