EXPERIMENTAL INVESTIGATION OF THE IMPACT PROBE METHOD FOR DETERMINING LOCAL SKIN FRICTION IN THE PRESENCE OF AN ADVERSE PRESSURE GRADIENT FOR A RANGE OF MACH NUMBERS FROM 1.70 TO 2.75.

Abstract

This thesis presents the results of an experimental program to determine the feasibility of using a surface impact probe to measure values of local skin friction in a turbulent boundary layer over a range of Mach Numbers and pressure gradients. This work is an extension of previous work on adverse pressure gradients which was done at a nominal Mach Number of 2.0. The present investigation was conducted on an adiabatic flat surface which formed the test-section floor of a variable Mach Number supersonic wind tunnel. The Mach Numbers ranged from 1.70 to 2.75 with adverse pressure gradients of zero to 1.57 psi/in. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1963
Accession Number
AD0457591

Entities

People

  • Oliver Hill

Organizations

  • University of Texas at Austin

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Friction
  • Layers
  • Mach Number
  • Pressure Gradients
  • Skin Friction
  • Supersonic Wind Tunnels
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow