FLUTTER MODEL TESTS OF ADVANCED WING CONFIGURATIONS AT INITIAL ANGLES OF ATTACK

Abstract

This report describes an experimental and analytical program conducted to determine the transonic and supersonic flutter boundary of a highly swept, low aspect ratio lifting surface typical of re-entry vehicle configurations. Several semi-rigid flutter models were constructed and tested at Mach numbers from .4 to 1.2 and also at Mach numbers from 2.0 to 5.0. The effects on flutter speed of initial angle of attack, un-coupled frequency ratio, model thickness ratio and a tip surface normal to the plane of the basic model were determined. The model aspect ratio was .889, the leading edge sweep angle was 70 degrees and the thickness ratio of the basic model was 6%. Other thicknesses were 3% and 9%. The cross-section of the model was modified wedge having a wedge angle in the streamwise direction of 22 degrees 38 minutes. The trailing edge was blunt. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1964
Accession Number
AD0355755

Entities

People

  • D. A. Brown

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aspect Ratio
  • Boundaries
  • Frequency
  • Leading Edges
  • Lifting Surfaces
  • Mach Number
  • Model Tests
  • Surfaces
  • Thickness
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow