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Scott L Schwimley

from Foristell, MO
Age ~65
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Also known as:
Scott Lee Schwimley, Scott Schwinley
Phone and address:
1417 Sycamore Lake Dr, Cappeln, MO 63348
(636) 398-5520
Related to:
John R Matchen, 70Jack C SchwimleyKarli A Schwimley, 32Barbara F PetrieJeanne C Schwimley, 95Kelsey Schwimley, 28Julie A Schwimley, 61Donald P Matchen, 65Brandon P Matchen, 29Robert F Petrie, 57Robert F Petrie
Connected to:
Burton L Schwimmer, 66Janna L Schwimmer, 60Joel Schwimmer, 44Leon Schwimmer, 49Lorna M Schwimmer, 41Philippe R Schwimmer, 51Samuel H Schwimmer, 76Jessica A Schwinck, 30Sally K Schwinck, 63Al W Schwindt, 78

Scott Schwimley Phones & Addresses

  • 1417 Sycamore Lake Dr, Foristell, MO 63348 (636) 398-5520
  • Westminster, MD
  • 608 Otter Creek Trl, Saint Peters, MO 63376 (636) 281-8337
  • 700 Providence Ln, Crystal Lake, IL 60012 (815) 477-2131 (847) 477-2131
  • 1411 Kingston Ln, Schaumburg, IL 60193
  • Berkeley, MO
  • Algonquin, IL
  • Fox Point, WI
  • Hazelwood, MO
  • McHenry, IL
  • Algonquin, IL
  • 1417 Sycamore Lake Dr, Foristell, MO 63348

Work

Company: Boeing Position: Engineering manager

Education

Degree: Master of Science, Bachelors, Masters, Master of Business Administration, Bachelor of Science School / High School: Park's College 1982 to 1985 Specialities: Engineering, Business

Emails

j***[email protected]

Industries

Aviation & Aerospace

Resumes

Resumes

Scott Schwimley Photo 1

Engineering Manager

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Location:
Foristell, MO
Industry:
Aviation & Aerospace
Work:
Boeing
Engineering Manager
Education:
Park's College 1982 - 1985
Master of Science, Bachelors, Masters, Master of Business Administration, Bachelor of Science, Engineering, Business

Business Records

Name / Title
Company / Classification
Phones & Addresses
Scott Schwimley
Owner
Schwimley's Outdoors
Ret Sporting Goods/Bicycles Mfg Leather Goods
700 Providence Ln, Bull Valley, IL 60012

Publications

Us Patents

Dynamic Bumps For Drag Reduction At Transonic-Supersonic Speeds

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US Patent:
8016245, Sep 13, 2011
Filed:
Oct 18, 2006
Appl. No.:
11/583140
Inventors:
Ahmed A. Hassan - Mesa AZ, US
Bradley A. Osborne - Manchester MO, US
Scott Schwimley - Foristell MO, US
Garry Billman - Troy MO, US
Mary Billman, legal representative - Troy MO, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 21/08
B64C 23/04
B64C 23/06
US Classification:
2442001, 2442041, 244208, 244130, 244 1 N
Abstract:
A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.

Plasma Actuator System And Method For Use With A Weapons Bay On A High Speed Mobile Platform

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US Patent:
8016246, Sep 13, 2011
Filed:
May 25, 2007
Appl. No.:
11/753869
Inventors:
Scott L. Schwimley - Foristell MO, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 21/00
B64C 23/00
US Classification:
244205, 244 1 N
Abstract:
A system and method for controlling a freestream air flow over a surface of an airborne mobile platform, for example an aircraft. In one implementation the system includes a plurality of plasma actuators used on an undersurface of a fuselage of an aircraft upstream of a weapons bay of the aircraft. When the plasma actuators are energized an induced flow is created adjacent the actuators. The induced flow operates to deflect the shear layer created when the freestream air flow moves over the weapons bay (while the bay doors are open), away from the weapons bay. This significantly reduces the oscillating acoustic pressure waves that would normally be produced if the shear layer turns into the weapons bay. The system and method significantly reduces acoustic noise inside the weapons bay and improves separation of ordnance from the weapons bay.

Plasma Flow Control Actuator System And Method

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US Patent:
8016247, Sep 13, 2011
Filed:
May 25, 2007
Appl. No.:
11/753876
Inventors:
Scott L. Schwimley - Foristell MO, US
Joseph S. Silkey - Florissant MO, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 21/00
US Classification:
244205, 244200
Abstract:
A plasma actuator system and method especially well adapted for use on airborne mobile platforms, such as aircraft, for directional and/or attitude control. The system includes at least one plasma actuator having first and second electrodes mounted on a surface of an aircraft. The first and second electrodes are arranged parallel to a boundary layer flow path over the surface. A third electrode is mounted between the first and second electrodes and laterally offset from the first and second electrodes. A high AC voltage signal is applied across the first and third electrodes, which induces a fluid flow between the energized electrodes that helps to delay separation of the boundary layer. Applying the AC voltage across the second and third electrodes causes an induced fluid flow that creates the opposite effect of influencing the boundary layer flow to separate from the surface. A plurality of the actuators can be selectively placed at various locations on the aircraft, and selectively energized to provide directional control and/or attitude control over the aircraft.

Aerodynamic Fan Control Effector

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US Patent:
20090230240, Sep 17, 2009
Filed:
Mar 13, 2008
Appl. No.:
12/047489
Inventors:
Bradley A. Osborne - Manchester MO, US
Scott L. Schwimley - Foristell MO, US
Assignee:
THE BOEING COMPANY - Seal Beach CA
International Classification:
B64C 9/00
US Classification:
244 87
Abstract:
A fan control effector for an aircraft comprises at least one blade configured to be pivotably deployable in a radially outward direction from a retracted position to a deployed position such that the blade extends out of the aircraft. The fan control effector may be mounted in a symmetrical arrangement about a longitudinal axis on opposing wings of the aircraft. Furthermore, the fan control effector may comprise any number of blades for independent deployment outwardly from the wing. The blades are configured to be angularly deployable along a direction that is non-parallel to the longitudinal axis of the aircraft. The blades may be configured to be deployable sequentially from the wing starting with an initial deployment of an aft-most one of the blades.

Systems And Methods For Alleviating Aircraft Loads With Plasma Actuators

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US Patent:
20100004799, Jan 7, 2010
Filed:
Jul 1, 2008
Appl. No.:
12/166199
Inventors:
Scott Lee Schwimley - Foristell MO, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
G06F 17/00
B64C 21/00
US Classification:
701 3, 244205
Abstract:
Systems and methods for alleviating aircraft loads with plasma actuators are disclosed. A method for operating an aircraft in accordance with a particular embodiment includes receiving an input corresponding to an aircraft component structural response to an aerodynamic load. The method can further include, based at least in part on the input corresponding to the aircraft component's structural response, reducing the structural response to the aerodynamic load by activating at least one plasma actuator carried by the aircraft, in accordance with one or more activation parameters.

Dielectric Barrier Discharge Flight Control System Through Modulated Boundary Layer Transition

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US Patent:
20130292511, Nov 7, 2013
Filed:
May 2, 2012
Appl. No.:
13/462170
Inventors:
Bradley A. Osborne - Chesterfield MO, US
Scott L. Schwimley - Foristell MO, US
Joseph S. Silkey - Florissant MO, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 21/00
US Classification:
244 751
Abstract:
An aerodynamic control system incorporates multiple Dielectric Barrier Discharge (DBD) flow control actuators adjacent a surface of an airborne vehicle in a path of laminar boundary layer flow over the surface. A control computer receives a control input and selectively distributes power to an activation array selected from the DBD flow control actuators for transition to a first operating condition tripping the laminar boundary layer at selected streamwise locations for turbulent flow. When the control computer removes the distributed power the DBD flow control actuators return to a second operating condition restoring the laminar boundary layer.
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Scott L Schwimley from Foristell, MO, age ~65 Get Report