NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighterFlow fields about a generic flighter model were computed using FL057, a 3-D, finite volume Euler code. Computed pressure coefficients, forces, and moments at several Mach numbers (0.6, 0.8, 1.2, 1.4, and 1.6) are compared with wind tunnel data over a wide range of angles of attack in order to determine the applicability of the code for the analysis of fighter configurations. Two configurations were studied, a wing-body and a wing-body-chine. FL057 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FL057 predictions were also accurate for some test conditions once the leading edge vortex became well established. At the subsonic speeds, FL057 predicted vortex breakdown earlier than that seen in the experimental results. Placing the chine on the forebody delayed the onset of bursting and improved the correlation between numerical and experimental data at the subsonic conditions.
Document ID
19920000793
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Goodsell, Aga M. (NASA Ames Research Center Moffett Field, CA, United States)
Melton, John E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:3156
A-90161
NASA-TP-3156
Accession Number
92N10011
Funding Number(s)
PROJECT: RTOP 505-60-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available