Laminar Design for Supersonic Civil Transport

Abstract

The paper presents a design methodology for supersonic wing Sections with hybrid laminar flow control. The approach is based on coupled Euler/boundary layer flow simulation and linear stability analysis for transition prediction. The investigations show that combinations of simple pressure distribution shapes can be used to optimize airfoils for maximum extent of laminar flow and hence minimum friction drag.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 2001
Accession Number
ADP011103

Entities

People

  • Achmed Traore

Organizations

  • German Aerospace Center

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Airfoils
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Drag
  • Friction
  • Geometry
  • Hypervelocity Flow
  • Laminar Flow
  • Layers
  • Military Aircraft
  • Pressure Distribution
  • Reynolds Number
  • Skin Friction
  • Transitions
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.
  • Robotics and Automation.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers