Effects of Vertical Tail Flexibility on the Aerodynamic Characteristics of a 0.03-Scale NASA Space Shuttle Orbiter at Mach Numbers from 0.90 to 1.55.

Abstract

A 0.03-scale model of the NASA Space Shuttle Orbiter utilizing a flexible and a rigid vertical tail was tested in the Propulsion Wind Tunnel, Transonic (16T) at free-stream Mach numbers from 0.90 to 1.55, free-stream dynamic pressures from 300 to 700 psf, angles of attack from -2 to 12 deg and angles of sideslip from -5 to 9 deg for speedbrake deflections of 25 and 55 deg, and rudder deflections of 0 and 10 deg. The objective of the test was to determine the effects of vertical tail flexibility on the static stability and control characteristics of the Orbiter vehicle.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Aug 29, 1978
Accession Number
ADA062377

Entities

People

  • J. A. Black

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Calibration
  • Data Reduction
  • Dynamic Pressure
  • Free Stream
  • Instrumentation
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Nomenclature
  • Resilience
  • Space Shuttles
  • Strain Gages
  • Test Facilities
  • Uncertainty
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Fluid Dynamics.
  • Marine Hydrodynamics

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers