Theoretical Method for Solution of Aerodynamic Forces on Thin Wings in Nonuniform Supersonic Stream with an Application to Tail Surfaces

Abstract

A theoretical method for obtaining the aerodynamic forces acting on a thin wing in an irrotational nonuniform supersonic stream is presented. The method, based on linearized theory, consists of a three-component superposition. The lift and the moments induced by the nonuniformity depend only on the wing plan-form boundary and on the vertical perturbation velocity of the free stream at each point of the plan-form area. Expressions are provided that permit lift and moment solutions for arbitrary plan forms and velocity distributions. The method is applied to determine lift and moments acting on a rectangular tail surface due to a spanwise parabolic distribution of upwash. Lift and moments due to a linear upwash distribution are also evaluated.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1948
Accession Number
ADA380722

Entities

People

  • Harold Mirels

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aspect Ratio
  • Bodies
  • Coordinate Systems
  • Delta Wings
  • Differential Equations
  • Equations
  • Flow
  • Flow Fields
  • Free Stream
  • Leading Edges
  • Mach Number
  • Partial Differential Equations
  • Thin Wings
  • Trailing Edges
  • Trailing Vortices
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers