Aeroelastic Stability Tests of Thin Cylindrical Shells at Supersonic Speeds (Follow-On Tests)

Abstract

Follow-on tests to an investigation to determine the dynamic characteristics of thin cylindrical shells were conducted. The model consisted of an ogive cylinder with the test shell located on the cylindrical portion of the model approximately 78 percent of the model length aft of the nose. Data were recorded at Mach numbers of 2.2 and 2.5 for 0-deg angle of attack and yaw. Flutter was induced on the 0.0020- and 0.0032-in.-thick shells by reducing the model cavity pressure. Boundary-layer measurements were also made at various boundary-layer blowing rates.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1969
Accession Number
AD0851095

Entities

People

  • Warren E. White

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Classification
  • Government Procurement
  • Governments
  • Instrumentation
  • Layers
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Precision
  • Supersonic Wind Tunnels
  • Test Facilities
  • United States
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow