Investigation Of The F117a Vortical Flow Characteristics Preliminary Results

Lógica	Matemáticas	Astronomía y Astrofísica	Física	Química	Ciencias de la Vida
Ciencias de la Tierra y Espacio	Ciencias Agrarias	Ciencias Médicas	Ciencias Tecnológicas	Antropología	Demografía
Ciencias Económicas	Geografía	Historia	Ciencias Jurídicas y Derecho	Lingüística	Pedagogía
Ciencia Política	Psicología	Artes y Letras	Sociología	Ética	Filosofía

Investigation of the F117A Vortical Flow Characteristics Preliminary Results

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

Descargar recurso

Detalles del recurso

$msg.ficha_linkToArchive: DSpace at MIT

$msg.ficha_details_description: 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.

$msg.ficha_details_authors: Vermeersch, Sabine -

$msg.ficha_details_id: 55304699

$msg.ficha_details_version: 1.0

$msg.ficha_details_status: Final

$msg.ficha_details_learningresourcetype: Technical Report -

$msg.ficha_details_interactivitytype: Expositivo

$msg.ficha_details_interactivitylevel: muy bajo

$msg.ficha_details_intendedenduserrole: Estudiante - Profesor - Autor -

$msg.ficha_details_structure: Atomic

$msg.ficha_details_cost: no

$msg.ficha_details_copyright: sí

: An error occurred on the license name.

$msg.ficha_details_requirements: Browser: Any -

$msg.ficha_details_relation: [References] ACDL Technical Reports;CFDL-TR-92-2

$msg.ficha_details_submissiondate: 24-may-2013

$msg.ficha_details_contact:

$msg.ficha_details_location:

$msg.ficha_otrosRecursos_autor

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

$msg.ficha_otrosRecursos_mismaColeccion

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...
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...
A Comparison of Numerical Schemes on Triangular and Quadrilateral Models
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...
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...

$msg.ficha_comments_title

No hay ninguna valoración para este recurso.Sea el primero en valorar este recurso.