INVESTIGATION OF DRAG REDUCTION BY BOUNDARYLAYER SUCTION ON A BODY OF REVOLUTION AT MACH NUMBERS 2.5, 3, AND 3.5

Abstract

Tests were conducted in the 40-in. supersonic tunnel of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary-layer suction for laminar flow control on a 9.2-in.diam body of revolution at Mach 2. 5, 3, and 3.5 with a Reynolds number range (based on boundarylayer rake location) from 9.9 to 51.7 million for angles of attack from 0 to =2 deg. The condition of the boundary layer was very sensitive to changes in angle of attack. Increasing the Reynolds number also decreased the maximum angle of attack. Wake, suction, and total drag coefficients and the corresponding suction coefficients are presented, along with some fully turbulent wake drag coefficients for the no suction case.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1965
Accession Number
AD0456988

Entities

People

  • S. R. Pate

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Counter IED

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Boundaries
  • Boundary Layer
  • Construction
  • Data Analysis
  • Drag Reduction
  • Flow
  • Free Stream
  • Instrumentation
  • Layers
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Static Pressure
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow