The Aerodynamics of Supersonic Biplanes of Finite Span

Abstract

Linearized supersonic-flow theory is employed to evaluate the lift and drag of biplane cellules having the 'Busemann-biplane configuration. The lift and drag are explicitly expressed as functions of thickness ratio and the angle of attack; the coefficients involved are universal for all Busemann biplane. Interpretation of the results for various Mach numbers is afforded by a similarity rule. Most of the results are presented graphically. It is found that the wave drag due to thickness of finite-span Busemann biplanes is small.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1950
Accession Number
ADA075884

Entities

People

  • H. S. Tan

Organizations

  • Cornell University College of Engineering

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Air Force
  • Air Force Facilities
  • Boundary Value Problems
  • Delta Wings
  • Differential Equations
  • Equations
  • Flow
  • Flow Fields
  • Free Stream
  • Integral Equations
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Trailing Edges
  • Two Dimensional
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Theoretical Analysis.

Technology Areas

  • Hypersonics