UNIFIED ANALYSIS OF AERODYNAMIC LOADS AT SUPERSONIC SPEEDS ON TRIANGULAR WINGS HAVING ARBITRARY CAMBER AND TWIST. VOLUME I,

Abstract

An investigation was performed by means of linearized supersonic flow theory to determine the distributed and integrated forces and moments on triangular wings. The downwashes considered are both symmetric and anti-symmetric in relation to the spanwise coordinate. The analysis excludes only the subsonic trailing edge condition. It is concluded that for delta wings of nearly equal chord and semi-span the camber has a very appreciable effect. This result is also indicated when the leading edges are subsonic and supersonic. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 20, 1956
Accession Number
AD0697865

Entities

People

  • Helen M. Grijalva
  • Julian H. Kainer

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Aircraft Wings
  • Airfoils
  • Airframes
  • Delta Wings
  • Downwash
  • Edges
  • Flow
  • Fluid Flow
  • Leading Edges
  • Supersonic Flow
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics