Force Tests on a Slotted Delta Wing with Varying Leading-Edge Camber at Supersonic Mach Numbers

Abstract

Tests were conducted in a 40-in. supersonic wind tunnel on a 70-deg- sweep delta wing. A gap between the leading edge and main body was varied from a sealed condition to a nominal 0.030-in. opening for three leading edges of various camber. The aerodynamic characteristics of these configurations were obtained at Mach numbers 1.5, 2.0, and 3.0 at angles of attack from -12 to 12 deg and Reynolds numbers, based on the 10-in. model root chord, from 1,300,000 to 6,000,000. Results are presented showing the variation in lift/drag for various combinations of gap width and leading-edge camber.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1968
Accession Number
AD0844666

Entities

People

  • E. J. Lucas
  • W. R. Martindale

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Characteristics
  • Air Force
  • Boundary Layer
  • Delta Wings
  • Drag
  • Dynamics
  • Free Stream
  • Gas Dynamics
  • Government Procurement
  • Governments
  • Instrumentation
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Supersonic Wind Tunnels
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow