Improving rudder effectiveness with sweeping jet actuators

Roman Seele; Emilio Graff; Morteza Gharib; Lutz Taubert; John Lin; Israel Wygnanski

doi:10.2514/6.2012-3244

Improving rudder effectiveness with sweeping jet actuators

Roman Seele, Emilio Graff, Morteza Gharib, Lutz Taubert, John Lin, Israel Wygnanski

Aerospace and Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

73 Scopus citations

Abstract

The application of active flow control on a vertical tail of a typical twin engine aircraft was investigated. Sweeping jets installed into the rudder surface were used and their effect was assessed by force measurements, flow visualization and local pressure distributions. The airfoil forming the tail is a NACA 0012 with a rudder using 35% of its chord. The tests were carried out at the Lucas Wind Tunnel at the California Institute of Technology at representative Reynolds numbers of up to Re=1.5 million. Multiple flap deflections and spanwise actuator configurations were tested resulting in an increase of up to 50-70% in side force depending on the free stream velocity and momentum input.

Original language	English (US)
Title of host publication	6th AIAA Flow Control Conference 2012
Publisher	American Institute of Aeronautics and Astronautics Inc.
ISBN (Print)	9781624101885
DOIs	https://doi.org/10.2514/6.2012-3244
State	Published - 2012
Event	6th AIAA Flow Control Conference 2012 - New Orleans, LA, United States Duration: Jun 25 2012 → Jun 28 2012

Publication series

Name	6th AIAA Flow Control Conference 2012

Other

Other	6th AIAA Flow Control Conference 2012
Country/Territory	United States
City	New Orleans, LA
Period	6/25/12 → 6/28/12

ASJC Scopus subject areas

Fluid Flow and Transfer Processes
Aerospace Engineering
Control and Systems Engineering

Access to Document

10.2514/6.2012-3244

Cite this

Seele, R, Graff, E, Gharib, M, Taubert, L, Lin, J & Wygnanski, I 2012, Improving rudder effectiveness with sweeping jet actuators. in 6th AIAA Flow Control Conference 2012. 6th AIAA Flow Control Conference 2012, American Institute of Aeronautics and Astronautics Inc., 6th AIAA Flow Control Conference 2012, New Orleans, LA, United States, 6/25/12. https://doi.org/10.2514/6.2012-3244

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abstract = "The application of active flow control on a vertical tail of a typical twin engine aircraft was investigated. Sweeping jets installed into the rudder surface were used and their effect was assessed by force measurements, flow visualization and local pressure distributions. The airfoil forming the tail is a NACA 0012 with a rudder using 35% of its chord. The tests were carried out at the Lucas Wind Tunnel at the California Institute of Technology at representative Reynolds numbers of up to Re=1.5 million. Multiple flap deflections and spanwise actuator configurations were tested resulting in an increase of up to 50-70% in side force depending on the free stream velocity and momentum input.",

author = "Roman Seele and Emilio Graff and Morteza Gharib and Lutz Taubert and John Lin and Israel Wygnanski",

year = "2012",

doi = "10.2514/6.2012-3244",

language = "English (US)",

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series = "6th AIAA Flow Control Conference 2012",

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PY - 2012

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N2 - The application of active flow control on a vertical tail of a typical twin engine aircraft was investigated. Sweeping jets installed into the rudder surface were used and their effect was assessed by force measurements, flow visualization and local pressure distributions. The airfoil forming the tail is a NACA 0012 with a rudder using 35% of its chord. The tests were carried out at the Lucas Wind Tunnel at the California Institute of Technology at representative Reynolds numbers of up to Re=1.5 million. Multiple flap deflections and spanwise actuator configurations were tested resulting in an increase of up to 50-70% in side force depending on the free stream velocity and momentum input.

AB - The application of active flow control on a vertical tail of a typical twin engine aircraft was investigated. Sweeping jets installed into the rudder surface were used and their effect was assessed by force measurements, flow visualization and local pressure distributions. The airfoil forming the tail is a NACA 0012 with a rudder using 35% of its chord. The tests were carried out at the Lucas Wind Tunnel at the California Institute of Technology at representative Reynolds numbers of up to Re=1.5 million. Multiple flap deflections and spanwise actuator configurations were tested resulting in an increase of up to 50-70% in side force depending on the free stream velocity and momentum input.

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M3 - Conference contribution

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Improving rudder effectiveness with sweeping jet actuators

Abstract

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