AN INVESTIGATION OF THE AEROELASTIC STABILITY OF THIN CYLINDRICAL SHELLS AT TRANSONIC MACH NUMBERS

Abstract

Static pressure and boundary-layer data were obtained over a rigid pressure shell at Mach numbers from 1.20 to 1.50 and Reynolds numbers from 1.04 to 4.20 x 10 to the 6th/ft in the 16-ft transonic tunnel. These data were obtained with and without addition of air into the boundary layer through a circular slot upstream of the test shell. Flutter characteristics of thin cylindrical shells were obtained at Mach numbers of 1.20 and 1.50 with and without boundary-layer blowing and shell axial loading. Spirally traveling waves appeared on three of the shells just prior to divergent flutter, which was initiated by reducing shell cavity pressure.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1966
Accession Number
AD0632829

Entities

People

  • T. M. Perkins
  • T. R. Brice

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Sensors

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Dynamic Pressure
  • Free Stream
  • Instrumentation
  • Layers
  • Mach Number
  • Measurement
  • Modulus Of Elasticity
  • Motion Pictures
  • Photographs
  • Pressure Distribution
  • Reynolds Number
  • Static Pressure
  • Traveling Waves
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • ballistics.