Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)

Abstract

STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and drag behavior of a NACA 0012 airfoil. Numerical solutions are obtained for a Mach number of 0.3 and a Reynolds number of one million. The parameters examined are angle of attack, fan ejection angle and suction velocity. The numerical code used is based on the Beam-Warming implicit factorization algorithm for solving the two- dimensional mass-averaged compressible Navier-Stokes equations for viscous, unsteady flows. Keywords: Drag reduction, Lift augmentation, Computational fluid dynamics, Mass transfer, Vectored blowing, Theses.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1988
Accession Number
ADA205771

Entities

People

  • Paul D. Boyles

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Cyber
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Mechanical Properties
  • Navier Stokes Equations
  • Reynolds Number
  • Short Takeoff Aircraft
  • Three Dimensional
  • Turbulent Mixing
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)