EXPANSION SIDE FLOW FIELD IMPACT PRESSURE SURVEYS OF A 75-DEG DELTA WING AT MACH NUMBER 10

Abstract

Impact pressure surveys were obtained in the leeward flow field of a 75-deg sharp leading-edge delta wing. Tests were conducted at a Mach number of 10.13, Reynolds number (based on model length) of 430,000, angles of attack of 15 and 19 deg, and zero sideslip angle. Abrupt pressure changes were observed in the flow field between the model surface and bow shock. Representative results are presented for alpha = 15 deg.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1968
Accession Number
AD0670512

Entities

People

  • C. J. Spurlin

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Bow Shock
  • Classification
  • Contracts
  • Delta Wings
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Government Procurement
  • Instrumentation
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Shock
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.