Propulsion System Integration and Test Program (Steady State). Part IV. Inlet Drag Tests.

Abstract

A wind tunnel test program was evolved for obtaining experimental performance data on a mach 2.5, two-dimensional, external compression inlet typical of the IPS Tactical Fighter inlet. Tests were conducted at mach numbers of 0.6, 0.85, 0.95, 1.2, 1.3, 1.7 and 2.2. The investigation was intended to provide the data necessary to evaluate installation effects and to substantiate analytic methods of performance predictions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0858916

Entities

People

  • Joel H. Huff Jr
  • Theodore J. Johnson

Tags

DTIC Thesaurus Topics

  • Compression
  • Mach Number
  • Physical Properties
  • Propulsion Systems
  • Steady State
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aviation Science / Aeronautics.
  • Fluid Dynamics.