NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Evaluation of Gritting Strategies for High Angle of Attack Using Wind Tunnel and Flight Test Data for the F/A-18A subsonic study of high-angle-of-attack gritting strategies was undertaken with a 0.06-scale model of the F/A-18, which was assumed to be typical of airplanes with smooth-sided forebodies. This study was conducted in the Langley 7- by 10-Foot High-Speed Tunnel and was intended to more accurately simulate flight boundary layer characteristics on the model in the wind tunnel than would be possible by using classical, low-angle-of-attack gritting on the fuselage. Six-component force and moment data were taken with an internally mounted strain-gauge balance, while pressure data were acquired by using electronically scanned pressure transducers. Data were taken at zero sideslip over an angle-of-attack range from 0 deg to 40 deg and, at selected angles of attack, over sideslip angles from -10 deg to 10 deg. Free-stream Mach number was fixed at 0.30, which resulted in a Reynolds number, based on mean aerodynamic chord, of 1.4 x 10(exp 6). Pressure data measured over the forebody and leading-edge extensions are compared to similar pressure data taken by a related NASA flight research program by using a specially instrumented F/A-18, the High-Alpha Research Vehicle (HARV). Preliminary guidelines for high-angle-of-attack gritting strategies are given.
Document ID
19980137574
Acquisition Source
Langley Research Center
Document Type
Technical Publication (TP)
Authors
Hall, Robert M. (NASA Langley Research Center Hampton, VA United States)
Erickson, Gary E. (NASA Langley Research Center Hampton, VA United States)
Fox, Charles H., Jr. (NASA Langley Research Center Hampton, VA United States)
Banks, Daniel W. (NASA Dryden Flight Research Center Edwards, CA United States)
Fisher, David F. (NASA Dryden Flight Research Center Edwards, CA United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1998
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60.207670
L-17562
NASA/TP-1998-207670
Funding Number(s)
PROJECT: RTOP 505-68-30-03
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