1) La descarga del recurso depende de la página de origen
2) Para poder descargar el recurso, es necesario ser usuario registrado en Universia

Opción 1: Descargar recurso

Detalles del recurso


The investigation of the vortical flow around the F117A Stealth Fighter is presented in order to demonstrate the capability to resolve leading edge vortices with an adaptive finite element solver for the Euler equations. The major goal is to capture vortex breakdown at high angles of attack. This work presents the five main steps involved in a typical study of the flow characteristics of a complete aircraft : the definition of the model geometry, the realization of a suitable grid around the discretized model, the implementation of a flow solver, the subsequent analysis of the flow field and the comparison to experimental data sets. The computational data are compared to the lift curves of the aircraft obtained in a subsonic 5' x 7' wind tunnel. The occurance and location of vortex breakdown is determined by performing flow visualization in the tunnel. Five cases are computed for this work. Each case is studied at Mach 0.3 and angles of attack range between 7 and 30 degrees.

Pertenece a

DSpace at MIT  


Vermeersch, Sabine - 

Id.: 55304699

Versión: 1.0

Estado: Final

Tipo de recurso: Technical Report  - 

Tipo de Interactividad: Expositivo

Nivel de Interactividad: muy bajo

Audiencia: Estudiante  -  Profesor  -  Autor  - 

Estructura: Atomic

Coste: no

Copyright: sí

: An error occurred on the license name.

Requerimientos técnicos:  Browser: Any - 

Relación: [References] ACDL Technical Reports;CFDL-TR-92-2

Fecha de contribución: 24-may-2013



Otros recursos del mismo autor(es)

  1. Investigation of the F117A vortical flow characteristics by Sabine Anne Vermeersch.

Otros recursos de la mismacolección

  1. Adaptive Mesh Euler Equation Computations of Vortex Breakdown in Delta Wing Flow A solution method for the three-dimensional Euler equations is formulated and implemented. The solve...
  2. System Identification and Active Control of a Turbulent Boundary Layer An experimental investigation is made into the active control of the near-wall region of a turbulent...
  3. A Comparison of Numerical Schemes on Triangular and Quadrilateral Models
  4. Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing Euler and Navier-Stokes results are presented for a blunt delta wing at Mach 7.15 and 300 angle of a...
  5. A Semi-Implicit Navier-Stokes Solver and Its Application to a Study of Separated Flow about Blunt Delta Wings A novel semi-implicit scheme for the Navier-Stokes equations is presented and evaluated. The semi-im...

Aviso de cookies: Usamos cookies propias y de terceros para mejorar nuestros servicios, para análisis estadístico y para mostrarle publicidad. Si continua navegando consideramos que acepta su uso en los términos establecidos en la Política de cookies.