Investigation of the F117A Vortical Flow Characteristics Preliminary Results
Name
CFDL-TR-92-2.pdf
Size
28.6 MB
Format
Adobe PDF
Checksum (MD5)
8672285d54b5b2a5206e451f10f4c1a9
Author(s)
Vermeersch, Sabine
Date Issued
October 1992
Publisher
Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology
Series/Report no.
ACDL Technical Reports;CFDL-TR-92-2
Abstract
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.
Terms of Use
An error occurred on the license name.
Persistent DSpace Link
