NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Flight tests of external modifications used to reduce blunt base dragThe effectiveness of a trailing disk (the trapped vortex concept) in reducing the blunt base drag of an 8-in diameter body of revolution was studied from measurements made both in flight and in full-scale wind-tunnel tests. The experiment demonstrated the significant base drag reduction capability of the trailing disk to Mach 0.93. The maximum base drag reduction obtained from a cavity tested on the flight body of revolution was not significant. The effectiveness of a splitter plate and a vented-wall cavity in reducing the base drag of a quasi-two-dimensional fuselage closure was studied from base pressure measurements made in flight. The fuselage closure was between the two engines of the F-111 airplane; therefore, the base pressures were in the presence of jet engine exhaust. For Mach numbers from 1.10 to 1.51, significant base drag reduction was provided by the vented-wall cavity configuration. The splitter plate was not considered effective in reducing base drag at any Mach number tested.
Document ID
19880053536
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Powers, Sheryll Goecke
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 88-2553
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Williamsburg, VA
Country: United States
Start Date: June 6, 1988
End Date: June 8, 1988
Accession Number
88A40763
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available