Results of Wind Tunnel Tests on a Flight Path Accelerometer at Mach Numbers from 0.2 to 3.0

Abstract

A program was conducted at the Arnold Engineering Development Center (AEDC) to design, fabricate, and test new full-scale angle-of-attack and sideslip vanes for the newly developed flight path accelerometer (FPA) to alleviate the dynamic stability problem of the previous vanes. The investigation was conducted in the von Karman Gas Dynamics Facility (VKF) Supersonic Wind Tunnel (A) and in the Propulsion Wind Tunnel Facility (PWT) Aerodynamic Wind Tunnel (4T). From dynamic stability tests of several vane configurations, the best performance vanes were selected and a position error calibration of Reynolds number rang based on boom diameter from 160,000 to 1,140,000. The angle of attack ranged from -3 to 24 deg. The selected vanes were dynamically stable over the entire Mach number range.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1972
Accession Number
AD0736819

Entities

People

  • James C. Uselton
  • T. O. Shadow

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Human Systems
  • Sensors

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Aspect Ratio
  • Calibration
  • Engineering
  • Flight
  • Flight Paths
  • Free Stream
  • Gas Dynamics
  • Instrumentation
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Reynolds Number
  • Sideslip
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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