A New Method for Designing Shock-Free Transonic Configurations.

Abstract

A new method for the design of shock-free supercritical airfoils, wings, and three-dimensional configurations is described. Results illustrating this procedure in two and three dimensions are given. They include modifications to part of the upper surface of an NACA 64A410 airfoil that will maintain shock-free flow over a range of Mach numbers for a fixed lift coefficient, and the modifications required on part of the upper surface of a swept wing with an NACA 64A410 root section to achieve shock-free flow. While the results are given for inviscid flow, the same procedures can be employed iteratively with a boundary layer calculation in order to achieve shock-free viscous designs. With a shock-free pressure field the boundary layer calculation will be reliable and not complicated by the difficulties of shock-wave boundary-layer interaction. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1978
Accession Number
ADA070888

Entities

People

  • A. R. Seebass
  • H. Sobieczky
  • K.-y. Fung
  • N. J. Yu

Organizations

  • University of Arizona

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aircraft Industry
  • Airfoils
  • Algorithms
  • Boundary Layer
  • Computational Fluid Dynamics
  • Engineering
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Inviscid Flow
  • Mach Number
  • Mechanical Engineering
  • Shock Waves
  • Swept Wings
  • Three Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design