Transonic and Low Supersonic Wind-Tunnel Tests on a Wing with Inboard Control Surface. Part I. General Description.

Abstract

A wind-tunnel investigation was carried out on a modified half-model of the F-5 wing with an oscillating in-board control surface. Detailed steady and unsteady pressure distributions were measured over the wing and over the control surface. Sectional as well as total coefficients for the wing and the control surface were obtained by integration of the measured pressure distributions. The tests covered the Mach number range between Ma square 0.6 and 1.25 with frequencies of the control surface of 20 and 40 Hz, which corresponds to a maximum reduced frequency of 0.4 at Ma square 0.6 and 0.215. This report (Part I) describes the general set-up of the experiments, while the test results in tabulated form are given in Part II. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1980
Accession Number
ADA097094

Entities

People

  • A. J. Persoon
  • P. Schippers
  • R. Roos

Organizations

  • National Aerospace Laboratory

Tags

DTIC Thesaurus Topics

  • Actuators
  • Air Force
  • Control Surfaces
  • Data Reduction
  • Free Stream
  • Frequency
  • Government Procurement
  • Hydraulic Actuators
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Test Sets
  • Transducers
  • Transfer Functions
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerospace Engineering
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow