INVESTIGATION OF DRAG REDUCTION BY BOUNDARYLAYER SUCTION ON A 50-DEGREE SWEPT TAPERED WING AT M (FREE-STREAM) EQUALS 2.5 TO 4

Abstract

Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundarylayer suction for laminar flow control on a tapered, three-dimensional, 50-deg swept supersonic wing. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds number range (based on boundary-layer rake location) from 4.3 to 19.5 million for angles of attack of zero and =3 deg. Wake drag, suction drag, and total drag coefficients and the corresponding suction coefficients are presented, along with fully turbulent wake drag coefficients for the no-suction case.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1964
Accession Number
AD0450195

Entities

People

  • S. R. Pate

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Coefficients
  • Data Analysis
  • Dynamics
  • Flow
  • Free Stream
  • Gas Dynamics
  • Geometry
  • Hypervelocity Flow
  • Laminar Flow
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Static Pressure
  • Three Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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