WO2005089212A3 - System and method for closed loop control of boundary layer shear stress - Google Patents

System and method for closed loop control of boundary layer shear stress Download PDF

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Publication number
WO2005089212A3
WO2005089212A3 PCT/US2005/008145 US2005008145W WO2005089212A3 WO 2005089212 A3 WO2005089212 A3 WO 2005089212A3 US 2005008145 W US2005008145 W US 2005008145W WO 2005089212 A3 WO2005089212 A3 WO 2005089212A3
Authority
WO
WIPO (PCT)
Prior art keywords
boundary layer
shear stress
hot film
film sensor
control device
Prior art date
Application number
PCT/US2005/008145
Other languages
French (fr)
Other versions
WO2005089212A2 (en
Inventor
Siva M Mangalam
Original Assignee
Tao Of Systems Integration Inc
Siva M Mangalam
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Tao Of Systems Integration Inc, Siva M Mangalam filed Critical Tao Of Systems Integration Inc
Publication of WO2005089212A2 publication Critical patent/WO2005089212A2/en
Publication of WO2005089212A3 publication Critical patent/WO2005089212A3/en

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D43/00—Arrangements or adaptations of instruments
    • B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0065—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0065—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid
    • F15D1/008—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid comprising fluid injection or suction means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Abstract

A system is provided for controlling boundary layer shear stress adjacent a surface over which a fluid stream has been established. The system comprises a boundary layer control device adapted for altering at least one flow characteristic within a boundary layer in a selected region of the surface. The system further comprises a shear stress measurement system comprising a hot film sensor arrangement having at least one hot film sensor element appliable to the surface in the selected region. The at least one hot film sensor element is connected to an anemometer circuit configured to provide a sensor signal corresponding to heat transfer from the associated hot film sensor to the fluid stream. The system also comprises a control module in communication with the anemometer arrangement and the boundary layer control device. The control module is adapted for receiving and processing sensor signals signal from the anemometer circuit and for providing input signals to the boundary layer control device.
PCT/US2005/008145 2004-03-12 2005-03-11 System and method for closed loop control of boundary layer shear stress WO2005089212A2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US55253904P 2004-03-12 2004-03-12
US60/552,539 2004-03-12
US11/076,274 2005-03-09
US11/076,274 US7302838B2 (en) 2004-03-12 2005-03-09 System and method for closed loop control of boundary layer shear stress

Publications (2)

Publication Number Publication Date
WO2005089212A2 WO2005089212A2 (en) 2005-09-29
WO2005089212A3 true WO2005089212A3 (en) 2007-02-08

Family

ID=34922276

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2005/008145 WO2005089212A2 (en) 2004-03-12 2005-03-11 System and method for closed loop control of boundary layer shear stress

Country Status (2)

Country Link
US (1) US7302838B2 (en)
WO (1) WO2005089212A2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8155794B2 (en) * 2007-05-09 2012-04-10 Tao Of Systems Integration, Inc. System and method for control of aeroelasticity effects
CN114624464B (en) * 2022-03-23 2022-12-20 北京航空航天大学 Non-contact hot film testing equipment and method for judging stability of rotor part of gas compressor

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6024119A (en) * 1998-04-20 2000-02-15 The United States Of America As Represented By The Secretary Of The Navy Flow control system having actuated elastomeric membrane
US6732579B2 (en) * 2002-10-08 2004-05-11 The United States Of America As Represented By The Secretary Of The Navy Turbulent boundary layer thickness estimation method and apparatus

Family Cites Families (18)

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Publication number Priority date Publication date Assignee Title
US4229725A (en) * 1978-05-12 1980-10-21 Reilly Richard J Wind shear warning system for aircraft
GB2066194B (en) * 1979-12-24 1983-07-27 Maris J M Method of predicting the approaching stall of an aircraft wing
US4932610A (en) * 1986-03-11 1990-06-12 The United States Of America As Represented By The United States National Aeronautics And Space Administration Active control of boundary layer transition and turbulence
US4727751A (en) * 1987-01-15 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Crossflow vorticity sensor
US4848153A (en) * 1988-06-07 1989-07-18 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method and apparatus for detecting laminar flow separation and reattachment
US4936146A (en) * 1988-06-07 1990-06-26 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method and apparatus for detecting laminar flow separation and reattachment
US5074147A (en) * 1990-03-08 1991-12-24 Analytical Services & Materials, Inc. Flow rate measuring apparatus
US5218863A (en) * 1991-10-28 1993-06-15 Mangalam Siva M Instrumentation system for determining flow stagnation points
US5209111A (en) * 1992-01-07 1993-05-11 The United States As Represented By The United States National Aeronautics And Space Administration Method of measuring cross-flow vortices by use of an array of hot-film sensors
US5299455A (en) * 1992-03-27 1994-04-05 Mangalam Siva M Method and instrumentation system for measuring airspeed and flow angle
US5796612A (en) * 1992-11-18 1998-08-18 Aers/Midwest, Inc. Method for flight parameter monitoring and control
US5600060A (en) * 1996-02-22 1997-02-04 The United States Of America As Represented By The Secretary Of The Navy Apparatus and method for computing unsteady flows by direct solution of the vorticity equation
US5890681A (en) * 1997-05-01 1999-04-06 The United States Of America As Represented By The Secretary Of The Navy Method for controlling microturbulence
US6134959A (en) * 1998-08-17 2000-10-24 Tao Of Systems Integration, Inc. Method for detecting flow bifurcation during sonic flow conditions
US6169496B1 (en) * 1998-12-09 2001-01-02 Exigent International, Inc. Banked flight stall warning device and method
US6390417B1 (en) * 1999-06-30 2002-05-21 Honda Giken Kogyo Kabushiki Kaisha Drag control system for flying machine, process for estimating drag of flying machine, boundary layer control system, and boundary layer control process
US6371414B1 (en) * 1999-07-16 2002-04-16 Lockheed Martin Corporation System and method for manipulating and controlling fluid flow over a surface
US6424923B1 (en) * 2000-09-29 2002-07-23 The United States Of America As Represented By The Secretary Of The Navy Method for computing three dimensional unsteady flows by solution of the vorticity equation on a Lagrangian mesh

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6024119A (en) * 1998-04-20 2000-02-15 The United States Of America As Represented By The Secretary Of The Navy Flow control system having actuated elastomeric membrane
US6732579B2 (en) * 2002-10-08 2004-05-11 The United States Of America As Represented By The Secretary Of The Navy Turbulent boundary layer thickness estimation method and apparatus

Also Published As

Publication number Publication date
US7302838B2 (en) 2007-12-04
US20050199052A1 (en) 2005-09-15
WO2005089212A2 (en) 2005-09-29

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