Fundamental Research on Advanced Techniques for Sonic Boom Suppression

Abstract

A multiphase theoretical investigation on predicting and alleviating sonic boom intensity is described. A new theory to predict sonic boom intensity on the ground from wind tunnel tests using normal size models (as opposed to the very small models presently used) was developed. A relatively easy method to determine aircraft contours with desirable finite pressure rise times is presented, as is a method to determine phantom body shapes with desirable pressure rise times which can be simulated by heat addition to the flow upstream of the aircraft. It is shown that a slotted nozzle engine exhaust has the unique capability to shift lift from the solid surface of the wing to the region behind the wing, with a resulting reduction in sonic boom intensity.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1972
Accession Number
AD0757273

Entities

People

  • B. H. Geothert
  • H. Gruschka
  • R. Kohl
  • S. N. Chaudhuri
  • Yulin Pan

Organizations

  • University of Tennessee Space Institute

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerospace Craft
  • Aircraft Equipment
  • Aircraft Industry
  • Aircrafts
  • Airframes
  • Axisymmetric Flow
  • Birds
  • Computer Programming
  • Computer Programs
  • Differential Equations
  • Fluid Dynamics
  • Integral Equations
  • Pressure Distribution
  • Test And Evaluation
  • Test Methods
  • Two Dimensional
  • Wind Tunnel Tests

Fields of Study

  • Physics

Readers

  • Acoustics.
  • Fluid Dynamics.
  • Systems Analysis and Design