PRESSURE DISTRIBUTION AND FLOW VISUALIZATION TESTS OF A 1.5 ELLIPTIC CONE AT MACH 10

Abstract

Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1963
Accession Number
AD0414567

Entities

People

  • A. D. Ray
  • R. L. Palko

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Data Reduction
  • Flow
  • Flow Separation
  • Free Stream
  • Government Procurement
  • High Angles
  • Instrumentation
  • Mach Number
  • Measuring Instruments
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Waves
  • Stagnation Pressure
  • Static Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Materials Science