Supersonic Flow Field Visualization Studies of the M (infinity) = 6 Price Waverider Planform

Abstract

PERSONIC TESTS OF THE CONICAL FLOW DERIVED M(infinity) =6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel, These tests are part of a continuing effort to study the characteristics of waverider configured vehicles, Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel, Tests at Mach numbers of M 1,7, 2,8 and 4 were attempted but flowfleld studies were only completed at M(infinity) = 4.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2001
Accession Number
ADA397447

Entities

People

  • Karl Garcia

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Autonomy

DTIC Thesaurus Topics

  • Aeronautics
  • Aircrafts
  • Boundary Layer
  • Cameras
  • Computational Fluid Dynamics
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Hypersonic Aircraft
  • Hypersonic Vehicles
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gages
  • Pressure Measurement
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow