WIND TUNNEL TESTS OF AN UNMANNED FOLDING DELTA-WING HYPERSONIC GLIDER. PART II. LATERAL STATIC STABILITY AND CONTROL AT MACH NUMBERS OF 0.80, 1.86, AND 2.87

Abstract

Tests were performed in the 18- by 18-inch supersonic wind tunnel on a 0.042-scale model of an unmanned, delta-wing hypersonic glider at Mach numbers of 0.80, 1.86, and 2.87. During this phase of testing the lateral characteristics were determined for both folded and unfolded configurations. The effectiveness of various locations and deflections of wing and body spoilers as a means of lateral control was determined. There was a wide variation in the effectiveness of this type of controller. Degree and direction of control varied with location, deflection, and Mach number. Two different sizes of vertical fins were tested. The larger fin contributed greater directional stability but detracted from dihedral effect. The most consistent spoiler performance was obtained with the larger fin. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1961
Accession Number
AD0270497

Entities

People

  • Norman G. Ziegler

Tags

Communities of Interest

  • Autonomy

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Deflection
  • Delta Wings
  • Directional
  • Hypersonic Glide Vehicles
  • Mach Number
  • Models
  • Scale Models
  • Supersonic Wind Tunnels
  • Unmanned
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Autonomy
  • Hypersonics
  • Hypersonics - Hypersonic Flow