SUPERSONIC WIND TUNNEL FLUTTER MODEL TESTS INCLUDING FREE-FLIGHT DATA FROM ADMITTANCE MEASUREMENTS

Abstract

Results of flutter model tests in the supersonic Mach number range of 1.5 to 3.0 on a series of representative high-speed models are presented. Cantilever model data and free-flight model data were obtained. The free-flight model data were obtained from a new method of testing. The method obtains free-flight flutter information from restrained models in the wind tunnel through use of mechanical admittance measurements. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1963
Accession Number
AD0336408

Entities

People

  • Frank G. Hyland
  • Gifford W. Asher

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Flight
  • Free Flight
  • Free Flight Models
  • Mach Number
  • Model Tests
  • Models
  • Supersonic Wind Tunnels
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow