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Effect of Target-type Thrust Reverser on Transonic Aerodynamic Characteristics of a Single-engine Fighter ModelA brief investigation of a target-type thrust reverser on a single-engine fighter model has been conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.20 to 1.05.At Mach numbers of 0.80, 0.92, and 1.05, a hydrogen peroxide turbojet-engine simulator was operated with the thrust reverser extended. The angle of attack was varied from 0 degrees to 5 degrees at these Mach numbers. The Reynolds number of the free stream, based on the mean aerodynamic chord, was about 5 x 10(6). It was estimated that reversed jet operations separated the model boundary-layer flow over the upper surface of the horizontal tail and upper part of the afterbody. This resulted in a positive pitch increment due to reversed jet operation. Jet-on operation also tended to stabilize the severe lateral oscillations which occurred with the reverser extended and the jet off. It appeared that these jet-off oscillations were the result of an alternating separation and reattachment of the flow on the rearmost portions of the fuselage afterbody.
Document ID
19930093726
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Swihert, John M
Date Acquired
August 16, 2013
Publication Date
January 13, 1958
Report/Patent Number
NACA-RM-L57J16
Accession Number
93R23018
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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