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Forebody tangential blowing for control at high angles of attackA feasibility study to determine if the use of tangential leading edge blowing over the forebody could produce effective and practical control of the F-18 HARV aircraft at high angles of attack was conducted. A simplified model of the F-18 configuration using a vortex-lattice model was developed to obtain a better understanding of basic aerodynamic coupling effects and the influence of forebody circulation on lifting surface behavior. The effect of tangential blowing was estimated using existing wind tunnel data on normal forebody blowing and analytical studies of tangential blowing over conical forebodies. Incorporation of forebody blowing into the flight control system was investigated by adding this additional yaw control and sideforce generating actuator into the existing F-18 HARV simulation model. A control law was synthesized using LQG design methods that would schedule blowing rates as a function of vehicle sideslip, angle of attack, and roll and yaw rates.
Document ID
19910020838
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Kroo, I.
(Stanford Univ. CA, United States)
Rock, S.
(Stanford Univ. CA, United States)
Roberts, L.
(Stanford Univ. CA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.26:188773
NASA-CR-188773
SU-JIAA-TR-101
Accession Number
91N30152
Funding Number(s)
CONTRACT_GRANT: NCC2-55
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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