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Impact of flow unsteadiness on maneuvers and loads of agile aircraftA program of airload measurements on a family of low-aspect-ratio delta wings with sharp leading edges, subjected to large amplitude pitch transients with angles of attack up to 90 deg, is reviewed. Even for small values of the pitch-rate parameter, representative of maneuvers anticipated for agile aircraft, the force and moment overshoots can exceed by 50 percent their steady-state values. This is explained in terms of the hysteretic behavior of the breakdown locations of leading-edge vortices. An approximate theoretical model is proposed which includes the breakdown hysteresis as part of a three-term representation of the unsteady chordwise load distribution.
Document ID
19890043393
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jarrah, M. Ameen
(Stanford Univ. CA, United States)
Ashley, Holt
(Stanford University CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 89-1282
Meeting Information
Meeting: AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference
Location: Mobile, AL
Country: United States
Start Date: April 3, 1989
End Date: April 5, 1989
Accession Number
89A30764
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-84-0099
CONTRACT_GRANT: NCA2-287
Distribution Limits
Public
Copyright
Other

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