'Trailing edge' diaporamas de présentation

Active Interrogation of Helicopter Rotor Faults Using Trailing Edge Flap Actuation

Active Interrogation of Helicopter Rotor Faults Using Trailing Edge Flap Actuation. Patricia Stevens Doctoral Candidate Mechanical Engineering Penn State University Doctoral Dissertation Defense April 2, 2001. Outline. Background & Motivation Objectives of Work Modeling Approach

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Use of Airbrakes and Approach Control

Use of Airbrakes and Approach Control. Airbrakes and spoilers. Airbrakes create additional drag . The further out they moved, the greater the effect. Airbrakes and spoilers. The high drag reduces the glide performance. Airbrakes and spoilers. ASK13 (in still air) Airbrakes closed 25:1

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Evektor Sport Star

In cooperation with Mid Island Air Service, Inc., Brookhaven, NY (Michael Bellenir, CFI). Evektor Sport Star. Preflight Inspection Procedures. Click mouse or press enter to begin. Lesson Objectives:.

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Hexagon Metrology

Alternate Method to Certify Grid Plates and Line Scales using a CMM with Chromatic Confocal Sensor verses Traditional Methods. Hexagon Metrology By: JHorwell Sr. Metrologist July 2013. What may I Learn or Why Listen?.

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D. Todd Griffith, PhD Sandia National Laboratories WIND TURBINE BLADE MANUFACTURE 2012

Large Rotor Development: Sandia 100-meter Blade Research. D. Todd Griffith, PhD Sandia National Laboratories WIND TURBINE BLADE MANUFACTURE 2012 28 November, 2012 Dusseldorf, Germany. Sandia Technical Report Number: SAND2012-8780C. Costs (traditional) System ~ $3/lb Blades ~ $6/lb.

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Chap.4

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Identification of the AC Leptons or double charged particles with the TRT.

Identification of the AC Leptons or double charged particles with the TRT. Oleg Bulekov, Anatoli Romaniouk MEPHI. Introduction: Leptons of the Almost Commutative (AC) model . Almost commutative geometry offers a specific way to unify general relativity, quantum mechanics

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AGENDA (PM)

AGENDA (PM) . Future Directions: Navy Essential Programs, 12:30 - 2:30 PM - Smart Structures Based Nonthermal Anti-Icing - Rotor Flowfield / Ship Airwake Coupling During Shipboard DI - Active Rotors for Enhanced Shipboard DI Operations

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530.418 Aerospace Structures and Materials Lecture 1: Intro and Terms

530.418 Aerospace Structures and Materials Lecture 1: Intro and Terms. Lockheed-Martin X-35 Joint Strike Fighter (JSF) The U.S. Department of Defense awarded Lockheed-Martin Corp. a contract that could be worth upwards of $200 billion to build its new radar-evading Joint Strike Fighter.

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LAV contribution to the NA62 trigger

LAV contribution to the NA62 trigger. Mauro Raggi, LNF ONLINE WG CERN 9/2/2011. LAV can help rejecting photons from p + p 0 decay and m LAV can provide Time ( Dt 500ps), Energy (20%), f position The LAV detector is able to provide all its information directly @ L0TP

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ara.bme.hu/~kristof/CFDjegyzet/

www.ara.bme.hu/~kristof/CFDjegyzet/. Drawing: Arc by three points (pressure side, suction side, leading edge) Arc by Centre (inlet outlet, trailing edge) Spline (periodic boundaries). Spline (4points). Arc by centre. Surface from sketches, Add Frozen. Create parts. Block/Create Block.

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LIFT

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Airplanes

Airplanes. Question:. As you ride in a jet airplane, the clouds are passing you at 600 mph. The air just in front of one of the huge jet engine intake ducts is traveling much faster than 600 mph. much slower than 600 mph. about 600 mph. Observations About Airplanes.

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Rocket Construction

Rocket Construction. Ou r Goal. Some questions: What do we hope to accomplish? What specification are required to accomplish this goal? How can we design to those specifications? What elements can we change with this rocket?. Parts of a Model Rocket. Body Tube Cylindrical cardboard tube

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Meteorology Air Masses & Fronts

Meteorology Air Masses & Fronts. Reference. From the Ground Up Chapter 6.6 & 6.7: Air Masses & Fronts Pages 140 - 147. Introduction. Giant air masses move around with the winds and rotate around pressure systems to bring different weather to areas.

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FEA of Vehicle Front Stabilizer Bar & Airfoil Design (Final Project)

FEA of Vehicle Front Stabilizer Bar & Airfoil Design (Final Project). Name: Antonio Sevilla & Sanh Si Course: ME 272 FEA Professor: Jose Granda Date: 12-20-06. Objectives.

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Practise questions

Practise questions. Answers later. Qs. 1 on VI.

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AATC/FDTC Discussion Group Benchmark Experiments for Computations of Airframe Noise

AATC/FDTC Discussion Group Benchmark Experiments for Computations of Airframe Noise. Meelan Choudhari and Miguel Visbal Aerospace Sciences Meeting, Reno, NV 01-07-2008. Overall Goal. Promote development of benchmark experiments + pertinent computations by multiple teams

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WING LOADING (W/S), SPAN LOADING (W/b) AND ASPECT RATIO (b 2 /S)

WING LOADING (W/S), SPAN LOADING (W/b) AND ASPECT RATIO (b 2 /S). Span loading (W/b), wing loading (W/S) and AR (b 2 /S) are related Zero-lift drag, D 0 is proportional to wing area Induced drag, D i , is proportional to square of span loading Take ratio of these drags, D i /D 0

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