Investigation of a Two-Step Nozzle in the Langley 11-Inch Hypersonic Tunnel

Abstract

Flow surveys have been made in the first of several nozzles to be investigated in the Langley 11-inch hypersonic tunnel. The nozzle was designed by the method of characteristics for a Mach number of 6.98. Two 2-dimensional steps were used: the first step expanded the air in the horizontal plane to a Mach number of 4.36 and the second in the vertical plane to a Mach number of 6.98. The test results showed that, although a maximum Mach number of about 6.5 was obtained, the flow in the test section was not sufficiently uniform for quantitative wind-tunnel test purposes. Deviations from the design flow were traced to the presence of a thick boundary layer which developed in the first step along the parallel walls.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1950
Accession Number
ADA380579

Entities

People

  • Charles H. Mclellan
  • Mitchel H. Bertram
  • Thomas W. Williams

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aeronautical Laboratories
  • Barometric Pressure
  • Boundary Layer
  • Flow
  • Free Stream
  • Heat Exchangers
  • High Pressure
  • Mach Number
  • Measurement
  • Pressure Gradients
  • Pressure Measurement
  • Stagnation Pressure
  • Stagnation Temperature
  • Static Pressure
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow