FREE FLIGHT EXPERIMENTAL INVESTIGATIONS OF THE EFFECT OF BOUNDARY LAYER COOLING ON TRANSITION

Abstract

Free flight tests were conducted in the NOL Pressurized Ballistics Range for the purpose of investigating boundary layer transition under the conditions of extreme boundary layer cooling. The tests were conducted on smooth, sharp-nosed, slender cones. The tests were conducted at a nominal Mach number of 3 and a free stream unit Reynolds number per foot of 11.8 x 10 to the 6th power. The ratio of wall to adiabatic recovery temperature varied between 0.22 and 0.27. The results agreed very closely with results from wind tunnel test conducted at similar conditions. These free flight tests seem to substantiate earlier results which indicate a destabilizing trend for laminar boundary layers subjected to extreme cooling.

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Document Details

Document Type
Technical Report
Publication Date
Sep 29, 1961
Accession Number
AD0271681

Entities

People

  • Norman W. Sheetz Jr.
  • W. C. Lyons Jr.

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Transition
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Flight
  • Free Stream
  • Geometry
  • Heat Transfer
  • Jet Propulsion
  • Laminar Boundary Layer
  • Mach Number
  • Measurement
  • Ordnance Laboratories
  • Surface Roughness
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Fluid Mechanics and Fluid Dynamics.