Aerodynamic Properties of Avian Flight as a Function of Wing Shape. Andrew March Charles Bradley Advisor: Ephrahim Garcia
|
|
|
- Silvester Flynn
- 7 years ago
- Views:
Transcription
1 Aerodynamic Properties of Avian Flight as a Function of Wing Shape Andrew March Charles Bradley Advisor: Ephrahim Garcia
2 Biomimetics The Fusion of Biology and Engineering Natural Selection as an optimization mechanism (Genetic Algorithm) No one s perfect Current Areas of Investigation Neural Networks for Computation Better Kevlar from Spiders Advances in Aircraft from Aves Quasi-static aerodynamic measurements of bird wings in a wind tunnel Computer Simulation
3 Principles of Aerodynamics (2D-Data) 2 CL Cd = cd + πear Usual lift curve, linear and demonstrates stall Drag versus Lift is parabolic Two components of drag: profile and induced Induced drag and vortex formation Limits aircraft spacing and cause of adverse yaw
4 Background in Birds Wing Anatomy Joints & Angles Feathering Macro Primaries Secondaries Coverts Micro Barbules Owl s Tattered Tips Flight Strategies Gliding Flapping
5 Raptors
6 Species Used in Data Collection Red-tailed Hawk (Buteo jamaicensis) Great Horned Owl (Bubo virginianus)
7 Experimental Setup Bio Kinetic Specimens Rigidity and Flexibility Original Goal Steel Wire for Joint Actuation and Stability No Airfoil Impact Force Measurements 6 DOF, Foil Strain Gauge, Force Balance Wind tunnel 4 x4 Cross Section Suction Driven, 50 Flow Development Speeds 7.7, 18.0, 28.8, 38.5 mph [3.4, 8.05,12.9, m/s] Davis Instruments Wind Speed Meter 0271 Visualization He Bubbles and Smoke
8 Results, Lift Red-tailed Hawk Great Horned Owl Non-conventional lifting curve No distinct stall, lift levels off Demonstrates Aeroelasticity of the wing, and twisting into the flow
9 Simulation Comparison: Aeroelasticity Comparison of owl wing to an airfoil with two torsional springs in Potential Flow The model predicts a coefficient of lift decrease similar to that observed with wing Potential Flow is an okay model because moment from drag is small, compared to moment from lift
10 Results, Wrist Angle Red-tailed Hawk Minimal effect Jumps are due to exposure of covert feathers Two trends because of aeroelasticity Low airspeeds lift/drag decreases Higher airspeeds lift/drag has a maximum
11 Results, Induced Drag Great Horned Owl Induced drag on Great Horned Owl is below theoretical! Net drag still positive Great Horned Owl has primaries fanned at wingtips Flow vortex around primaries generates thrust.
12 Applications In 1987, J.J. Spillman showed wingtip sails (like primary feathers on bird wings) could reduce the drag substantially on aircraft Provided the sail is small it will experience a thrust offsetting the lift-dependent drag on the wing, He estimated a fuel savings of $200,000 per commercial jet per year Approximately $700,000 today! The sails were a detriment at flight regimes other than they were designed for Passive shape change and aeroelasticity could be the solution needed to minimize induced drag on modern aircraft Spillman, J.J; 1987, Wing Tip Sails, Progress to Date and Future Developments. Aeronautical Journal, vol 91, pp , December 1987.
13 Conclusion Current aircraft are only optimized for one flight regime Birds can completely alter their form to be in an optimum configuration in any regime The measurement of the forces on bird wings in different configurations is the first step towards morphing aircraft Passive shape change may play an essential role in mitigating induced drag and vortex formation NASA concept of morphing aircraft
14 Questions? Andrew March, Charles Bradley, Advisor: Ephrahim Garcia Ph.D.,
Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412
, July 2-4, 2014, London, U.K. Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412 Arvind Prabhakar, Ayush Ohri Abstract Winglets are angled extensions or vertical projections
Design and Structural Analysis of the Ribs and Spars of Swept Back Wing
Design and Structural Analysis of the Ribs and Spars of Swept Back Wing Mohamed Hamdan A 1, Nithiyakalyani S 2 1,2 Assistant Professor, Aeronautical Engineering & Srinivasan Engineering College, Perambalur,
Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids
Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids Dr. J. M. Meyers Dr. D. G. Fletcher Dr. Y. Dubief 1. Introduction In this lab the characteristics of airfoil lift, drag,
Design and Analysis of Spiroid Winglet
Design and Analysis of Spiroid Winglet W.GiftonKoil Raj 1, T.AmalSeba Thomas 2 PG Scholar, Dept of Aeronautical Engineering, Hindustan Institute of Technology and Science, Chennai, India 1 Assistant Professor,
A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic
AiMT Advances in Military Technology Vol. 8, No. 1, June 2013 Aerodynamic Characteristics of Multi-Element Iced Airfoil CFD Simulation A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty
The Avian Skeleton. Avian Flight. The Pelvic Girdle. Skeletal Strength. The Pelvic Girdle
Flight is the central avian adaptation Birds can fly at great speeds, for extended distances and time periods, can soar for days, and hover, fly upside down, and backwards Adaptations for flight are integrated
Requirements to servo-boosted control elements for sailplanes
Requirements to servo-boosted control elements for sailplanes Aerospace Research Programme 2004 A. Gäb J. Nowack W. Alles Chair of Flight Dynamics RWTH Aachen University 1 XXIX. OSTIV Congress Lüsse, 6-136
CAMRAD II COMPREHENSIVE ANALYTICAL MODEL OF ROTORCRAFT AERODYNAMICS AND DYNAMICS
CAMRAD II COMPREHENSIVE ANALYTICAL MODEL OF ROTORCRAFT AERODYNAMICS AND DYNAMICS 1 CAMRAD II IS AN AEROMECHANICAL ANALYSIS OF HELICOPTERS AND ROTORCRAFT INCORPORATING ADVANCED TECHNOLOGY multibody dynamics
XFlow CFD results for the 1st AIAA High Lift Prediction Workshop
XFlow CFD results for the 1st AIAA High Lift Prediction Workshop David M. Holman, Dr. Monica Mier-Torrecilla, Ruddy Brionnaud Next Limit Technologies, Spain THEME Computational Fluid Dynamics KEYWORDS
NACA 2415- FINDING LIFT COEFFICIENT USING CFD, THEORETICAL AND JAVAFOIL
NACA 2415- FINDING LIFT COEFFICIENT USING CFD, THEORETICAL AND JAVAFOIL Sarfaraj Nawaz Shaha 1, M. Sadiq A. Pachapuri 2 1 P.G. Student, MTech Design Engineering, KLE Dr. M S Sheshgiri College of Engineering
NACA Nomenclature NACA 2421. NACA Airfoils. Definitions: Airfoil Geometry
0.40 m 0.21 m 0.02 m NACA Airfoils 6-Feb-08 AE 315 Lesson 10: Airfoil nomenclature and properties 1 Definitions: Airfoil Geometry z Mean camber line Chord line x Chord x=0 x=c Leading edge Trailing edge
APPENDIX 3-B Airplane Upset Recovery Briefing. Briefing. Figure 3-B.1
APPENDIX 3-B Airplane Upset Recovery Briefing Industry Solutions for Large Swept-Wing Turbofan Airplanes Typically Seating More Than 100 Passengers Briefing Figure 3-B.1 Revision 1_August 2004 Airplane
APP Aircraft Performance Program Demo Notes Using Cessna 172 as an Example
APP Aircraft Performance Program Demo Notes Using Cessna 172 as an Example Prepared by DARcorporation 1. Program Layout & Organization APP Consists of 8 Modules, 5 Input Modules and 2 Calculation Modules.
Wing Design: Major Decisions. Wing Area / Wing Loading Span / Aspect Ratio Planform Shape Airfoils Flaps and Other High Lift Devices Twist
Wing Design: Major Decisions Wing Area / Wing Loading Span / Aspect Ratio Planform Shape Airfoils Flaps and Other High Lift Devices Twist Wing Design Parameters First Level Span Area Thickness Detail Design
Provided by TryEngineering - www.tryengineering.org
Provided by TryEngineering - Lesson Focus Lesson focuses on wind tunnel tests that engineers in many industries use to when developing products such as airplanes, cars, and even buildings. Teams of students
Understanding High Advance Ratio Flight
Alfred Gessow Rotorcraft Center University of Maryland Understanding High Advance Ratio Flight Graham Bowen-Davies Graduate Research Assistant Adviser: Inderjit Chopra Alfred Gessow Professor and Director
High-Lift Systems. High Lift Systems -- Introduction. Flap Geometry. Outline of this Chapter
High-Lift Systems Outline of this Chapter The chapter is divided into four sections. The introduction describes the motivation for high lift systems, and the basic concepts underlying flap and slat systems.
Messina Bridge History MULTI-BOX STEEL DECKS AND SUSPENSION SYSTEM FOR VERY LONG SPAN BRIDGES THE STRAIT OF MESSINA CROSSING 1968 International competition of ideas announced by the Italian national roads
CFD analysis for road vehicles - case study
CFD analysis for road vehicles - case study Dan BARBUT*,1, Eugen Mihai NEGRUS 1 *Corresponding author *,1 POLITEHNICA University of Bucharest, Faculty of Transport, Splaiul Independentei 313, 060042, Bucharest,
Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics
Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics 6.11 General discussions on control surface 6.11.1 Aerodynamic balancing 6.11.2 Set back hinge or over hang balance 6.11.3 Horn balanace
Experimental Wind Turbine Aerodynamics Research @LANL
Experimental Wind Turbine Aerodynamics Research @LANL B. J. Balakumar, Los Alamos National Laboratory Acknowledgment: SuhasPol(Post-doc), John Hoffman, Mario Servin, Eduardo Granados (Summer students),
HALE UAV: AeroVironment Pathfinder
HALE UAV: AeroVironment Pathfinder Aerodynamic and Stability Analysis Case Study: Planform Optimization Desta Alemayehu Elizabeth Eaton Imraan Faruque Photo courtesy NASA Dryden Photo Gallery 1 Pathfinder
Aerospace Engineering 3521: Flight Dynamics. Prof. Eric Feron Homework 6 due October 20, 2014
Aerospace Engineering 3521: Flight Dynamics Prof. Eric Feron Homework 6 due October 20, 2014 1 Problem 1: Lateral-directional stability of Navion With the help of Chapter 2 of Nelson s textbook, we established
Flight path optimization for an airplane
Flight path optimization for an airplane Dorothée Merle Master's Thesis Submission date: June 2011 Supervisor: Per-Åge Krogstad, EPT Norwegian University of Science and Technology Department of Energy
Risø-R-1374(EN) Design of a 21 m Blade with Risø-A1 Airfoils for Active Stall Controlled Wind Turbines
Risø-R-1374(EN) Design of a 21 m Blade with Risø-A1 Airfoils for Active Stall Controlled Wind Turbines Peter Fuglsang, Risø National Laboratory Ole Sangill, Norwin A/S Peter Hansen, LM Glasfiber A/S Risø
Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA. CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design
Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design Background Introduction ATS Company Background New and
FLow pattern around cable and its aerodynamic characteristics in critical Reynolds number range
The 22 World Congress on Advances in Civil, Environmental, and Materials Research (ACEM 2) Seoul, Korea, August 26-3, 22 FLow pattern around cable and its aerodynamic characteristics in critical Reynolds
AE 430 - Stability and Control of Aerospace Vehicles
AE 430 - Stability and Control of Aerospace Vehicles Atmospheric Flight Mechanics 1 Atmospheric Flight Mechanics Performance Performance characteristics (range, endurance, rate of climb, takeoff and landing
CFD Lab Department of Engineering The University of Liverpool
Development of a CFD Method for Aerodynamic Analysis of Large Diameter Horizontal Axis wind turbines S. Gomez-Iradi, G.N. Barakos and X. Munduate 2007 joint meeting of IEA Annex 11 and Annex 20 Risø National
ENHANCEMENT OF AERODYNAMIC PERFORMANCE OF A FORMULA-1 RACE CAR USING ADD-ON DEVICES B. N. Devaiah 1, S. Umesh 2
ENHANCEMENT OF AERODYNAMIC PERFORMANCE OF A FORMULA-1 RACE CAR USING ADD-ON DEVICES B. N. Devaiah 1, S. Umesh 2 1- M. Sc. [Engg.] Student, 2- Asst. Professor Automotive and Aeronautical Engineering Department,
CFD Analysis on Airfoil at High Angles of Attack
CFD Analysis on Airfoil at High Angles of Attack Dr.P.PrabhakaraRao¹ & Sri Sampath.V² Department of Mechanical Engineering,Kakatiya Institute of Technology& Science Warangal-506015 1 chantifft@rediffmail.com,
Performance. 13. Climbing Flight
Performance 13. Climbing Flight In order to increase altitude, we must add energy to the aircraft. We can do this by increasing the thrust or power available. If we do that, one of three things can happen:
Thin Airfoil Theory. Charles R. O Neill School of Mechanical and Aerospace Engineering Oklahoma State University Stillwater, OK 74078
13 Thin Airfoil Theory Charles R. O Neill School of Mechanical and Aerospace Engineering Oklahoma State University Stillwater, OK 7478 Project One in MAE 3253 Applied Aerodynamics and Performance March
A NUMERICAL METHOD TO PREDICT THE LIFT OF AIRCRAFT WINGS AT STALL CONDITIONS
Braz. Soc. of Mechanical Sciences and Engineering -- ABCM, Rio de Janeiro, Brazil, Nov. 29 -- Dec. 3, 24 A NUMERICAL METHOD TO PREDICT THE LIFT OF AIRCRAFT WINGS AT STALL CONDITIONS Marcos A. Ortega ITA
The aerodynamic center
The aerodynamic center In this chapter, we re going to focus on the aerodynamic center, and its effect on the moment coefficient C m. 1 Force and moment coefficients 1.1 Aerodynamic forces Let s investigate
Circulation Control NASA activities
National Aeronautics and Space Administration Circulation Control NASA activities Dr. Gregory S. Jones Dr. William E. Millholen II Research Engineers NASA Langley Research Center Active High Lift and Impact
Lecture 8 : Dynamic Stability
Lecture 8 : Dynamic Stability Or what happens to small disturbances about a trim condition 1.0 : Dynamic Stability Static stability refers to the tendency of the aircraft to counter a disturbance. Dynamic
Introduction to Flight
Introduction to Flight Sixth Edition John D. Anderson, Jr. Curator for Aerodynamics, National Air and Space Museum Smithsonian Institution Professor Emeritus University of Maryland Boston Burr Ridge, IL
Behavioral Animation Simulation of Flocking Birds
Behavioral Animation Simulation of Flocking Birds Autonomous characters determine their actions Simulating the paths of individuals in: flocks of birds, schools of fish, herds of animals crowd scenes 1.
GLIDING BIRDS: REDUCTION OF INDUCED DRAG BY WING TIP SLOTS BETWEEN THE PRIMARY FEATHERS
J. exp. Biol. 180, 285-310 (1993) Printed in Great Britain The Company of Biologists Limited 1993 285 GLIDING BIRDS: REDUCTION OF INDUCED DRAG BY WING TIP SLOTS BETWEEN THE PRIMARY FEATHERS VANCE A. TUCKER
LOCKHEED GEORGIA LOWSPEED WIND TUNNEL HONDA CIVIC HATCHBACK AIRTAB(R) MODIFICATION RESULTS
LOCKHEED GEORGIA LOWSPEED WIND TUNNEL HONDA CIVIC HATCHBACK AIRTAB(R) MODIFICATION RESULTS Executive Summary: This report shows conclusively that the Airtab product reduced aerodynamic drag forces at the
CFD simulations of flow over NASA Trap Wing Model
CFD simulations of flow over NASA Trap Wing Model Andy Luo Swift Engineering Pravin Peddiraju, Vangelis Skaperdas BETA CAE Systems Introduction A cooperative study was undertaken by BETA and Swift Engineering
NACA airfoil geometrical construction
The NACA airfoil series The early NACA airfoil series, the 4-digit, 5-digit, and modified 4-/5-digit, were generated using analytical equations that describe the camber (curvature) of the mean-line (geometric
Comparison between OpenFOAM CFD & BEM theory for variable speed variable pitch HAWT
ITM Web of Conferences 2, 05001 (2014) DOI: 10.1051/itmconf/20140205001 C Owned by the authors, published by EDP Sciences, 2014 Comparison between OpenFOAM CFD & BEM theory for variable speed variable
Experimental investigation of golf driver club head drag reduction through the use of aerodynamic features on the driver crown
Available online at www.sciencedirect.com Procedia Engineering 00 (2013) 000 000 www.elsevier.com/locate/procedia The 2014 conference of the International Sports Engineering Association Experimental investigation
Computational Modeling of Wind Turbines in OpenFOAM
Computational Modeling of Wind Turbines in OpenFOAM Hamid Rahimi hamid.rahimi@uni-oldenburg.de ForWind - Center for Wind Energy Research Institute of Physics, University of Oldenburg, Germany Outline Computational
Light Aircraft Design
New: Sport Pilot (LSA) The Light Aircraft Design Computer Program Package - based on MS-Excelapplication was now extented with the new Sport Pilots (LSA) loads module, which includes compliance for the
Basics of vehicle aerodynamics
Basics of vehicle aerodynamics Prof. Tamás Lajos Budapest University of Technology and Economics Department of Fluid Mechanics University of Rome La Sapienza 2002 Influence of flow characteristics on the
Figure 3. Pressure taps distribution around the bus model (64 pressure taps)
Figure1. Double deck bus into the wind tunnel The aerodynamic balance, built by the authors according Tusche [11], is based on strain gage type cells arranged as a double Wheatstone bridge acquiring simultaneously
The most exciting benefit of the GENESIS Conversion, by D Shannon is that it comes with a Maximum Gross Take-off Weight of 4000 lb.
Webster s Dictionary defines the word Genesis as forming, combining form meaning origination, creation, formation, evolution. In short, we have combined a number of our existing Bonanza modifications to
MICRO AERIAL VEHICLE DEVELOPMENT: DESIGN, COMPONENTS, FABRICATION, AND FLIGHT-TESTING
MICRO AERIAL VEHICLE DEVELOPMENT: DESIGN, COMPONENTS, FABRICATION, AND FLIGHT-TESTING Gabriel Torres and Thomas J. Mueller 117 Hessert Center, University of Notre Dame Notre Dame, IN 46556 Phone: (219)
parts of an airplane Getting on an Airplane BOX Museum Aeronautics Research Mission Directorate in a Series
National Aeronautics and Space Administration GRADES K-2 Aeronautics Research Mission Directorate Museum in a BOX Series www.nasa.gov parts of an airplane Getting on an Airplane MUSEUM IN A BOX Getting
Programme Discussions Wissenschaftstag Braunschweig 2015 Laminarität für zukünftige Verkehrsflugzeuge
Programme Discussions Wissenschaftstag Braunschweig 2015 Kevin Nicholls, EIVW Prepared by Heinz Hansen TOP-LDA Leader, ETEA Presented by Bernhard Schlipf, ESCRWG Laminarität für zukünftige Verkehrsflugzeuge
High-Speed Demonstration of Natural Laminar Flow Wing & Load Control for Future Regional Aircraft through innovative Wind Tunnel Model
High-Speed Demonstration of Natural Laminar Flow Wing & Load Control for Future Regional Aircraft through innovative Wind Tunnel Model Project organization The project tackles the CfP JTI-CS-2012-1-GRA-02-019
Hydrodynamic Loads on Two-Dimensional Sheets of Netting within the Range of Small Angels of Attack
Hydrodynamic Loads on Two-Dimensional Sheets of Netting within the Range of Small Angels of Attack by Mathias Paschen & Karsten Breddermann 10 th International Workshop Methods for the Development and
CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS
CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS K.Harish Kumar 1, CH.Kiran Kumar 2, T.Naveen Kumar 3 1 M.Tech Thermal Engineering, Sanketika Institute of Technology & Management,
Practice Problems on Boundary Layers. Answer(s): D = 107 N D = 152 N. C. Wassgren, Purdue University Page 1 of 17 Last Updated: 2010 Nov 22
BL_01 A thin flat plate 55 by 110 cm is immersed in a 6 m/s stream of SAE 10 oil at 20 C. Compute the total skin friction drag if the stream is parallel to (a) the long side and (b) the short side. D =
CFD results for TU-154M in landing configuration for an asymmetrical loss in wing length.
length. PAGE [1] CFD results for TU-154M in landing configuration for an asymmetrical loss in wing length. Summary: In CFD work produced by G. Kowaleczko (GK) and sent to the author of this report in 2013
Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in Wind Turbines and Wind Tunnels
NASA/CR 2008-215434 Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in Wind Turbines and Wind Tunnels David A. Spera Jacobs Technology, Inc., Cleveland, Ohio An errata was added
Learning objectives 5.2 Principles of Flight - Helicopter
082 00 00 00 PRINCIPLES OF FLIGHT HELICOPTER 082 01 00 00 SUBSONIC AERODYNAMICS 082 01 01 00 Basic concepts, laws and definitions 082 01 01 01 SI Units and conversion of units PPL: Conversion of units
Flap Optimization for Take-off and Landing
Proceedings of the 10th Brazilian Congress of Thermal Sciences and Engineering -- ENCIT 2004 Braz. Soc. of Mechanical Sciences and Engineering -- ABCM, Rio de Janeiro, Brazil, Nov. 29 -- Dec. 03, 2004
Development and Design of a Form- Adaptive Trailing Edge for Wind Turbine Blades
Development and Design of a Form- Adaptive Trailing Edge for Wind Turbine Blades Master Thesis Alireza Taheri REMENA Batch 5 Matriculation Number - 33105532 Institut Thermische Energietechnik 10.02.2015
Platform Technology for Computational Fluid Dynamics Supporting Design of System Products
Hitachi Review Vol. 61 (2012), No. 6 244 Platform Technology for Computational Fluid Dynamics Supporting Design of System Products from Power Plants and Industrial Machinery to Home Appliances Shigehisa
1.0 Background 1.1 Historical background 1.2 Cost of wind turbines
1.0 Background 1.1 Historical background Wind energy has been used for thousands of years for milling grain, pumping water and other mechanical power applications. Wind power is not a new concept. The
Engine Yaw Augmentation for Hybrid-Wing-Body Aircraft via Optimal Control Allocation Techniques
AIAA Guidance, Navigation, and Control Conference 08-11 August 2011, Portland, Oregon AIAA 2011-6253 Engine Yaw Augmentation for Hybrid-Wing-Body Aircraft via Optimal Control Allocation Techniques Brian
Faculty of Aerospace Engineering
Delft University of Technology Dr. ir. Roeland De Breuker and Dr. Arvind Rao 20-3-2013 Delft University of Technology Challenge the future Delft University of Technology General Information Founded in
AERODYNAMIC ANALYSIS OF BLADE 1.5 KW OF DUAL ROTOR HORIZONTAL AXIS WIND TURBINE
AERODYNAMIC ANALYSIS OF BLADE 1.5 KW OF DUAL ROTOR HORIZONTAL AXIS WIND TURBINE HITENDRA KURMI Research scholar, School of Energy and Environmental Managment,UTD, RGPV Bhopal,MP,INDIA htr.ptl@gmail.com
Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT
Adam Dziubiński CFD group IoA FLUENT Content Fluent CFD software 1. Short description of main features of Fluent 2. Examples of usage in CESAR Analysis of flow around an airfoil with a flap: VZLU + ILL4xx
QUT Digital Repository: http://eprints.qut.edu.au/
QUT Digital Repository: http://eprints.qut.edu.au/ El-Atm, Billy and Kelson, Neil A. and Gudimetla, Prasad V. (2008) A finite element analysis of the hydrodynamic performance of 3- and 4-Fin surfboard
Wind Energy at Earth Sciences
Wind Energy at Earth Sciences Associate Professor Stefan Ivanell Director Wind Energy UU and KTH Wind Centre Outlook About Wind Energy An overview of research activities Wake studies Wind Energy Andrew
Numerical simulation of maneuvering combat aircraft
Numerical simulation of maneuvering combat aircraft Andreas Schütte DLR - German Aerospace Center Institute of Aerodynamics and Flow Technology Oct. 14 th 2005, Stuttgart Folie 1 > HLRS 2005 > A. Schütte
RenaissanceRe Wall of Wind Research -- Moving Innovations from Theory to Applications
RenaissanceRe Wall of Wind Research -- Moving Innovations from Theory to Applications by Arindam Gan Chowdhury, PhD Director, Laboratory for Wind Engineering Research, International Hurricane Research
PARAMETRIC INVESTIGATION OF A HIGH-LIFT AIRFOIL AT HIGH REYNOLDS NUMBERS. John C. Lin* NASA Langley Research Center, Hampton, VA 23681-0001.
PARAMETRIC INVESTIGATION OF A HIGH-LIFT AIRFOIL AT HIGH REYNOLDS NUMBERS John C. Lin* NASA Langley Research Center, Hampton, VA 23681-0001 and Chet J. Dominik McDonnell Douglas Aerospace, Long Beach, CA
How do sails work? Article by Paul Bogataj
How do sails work? Article by Paul Bogataj Sails are wings that use the wind to generate a force to move a boat. The following explanation of how this occurs can help understand how to maximize the performance
Fundamentals of Airplane Flight Mechanics
Fundamentals of Airplane Flight Mechanics David G. Hull Fundamentals of Airplane Flight Mechanics With 125 Figures and 25 Tables 123 David G. Hull The University of Texas at Austin Aerospace Engineering
Name That Adaptation. Background: Link to the Plan Read Section 5 (Whooping Crane Ecology and Biology) in the Management Plan
Summary Students will explore structural, physiological, and behavioral adaptations of whooping cranes. Objectives: Students will be able to: Define an adaptation Describe several whooping crane adaptations
To provide insight into the physics of arrow flight and show how archers adapt their equipment to maximize effectiveness.
The Science of Archery Godai Katsunaga Purpose To provide insight into the physics of arrow flight and show how archers adapt their equipment to maximize effectiveness. Archery Archery is one of the events
13.021 Marine Hydrodynamics Lecture 24B Lifting Surfaces. Introduction What are the characteristics of a lifting surface?
13.021 Marine Hydrodynamics Lecture 24B Lifting Surfaces Introduction What are the characteristics of a lifting surface? Lifting surfaces in marine hydrodynamics typically have many applications such as
Aerodynamics at Volvo Car Corporation KTH 2008
Aerodynamics at Volvo Car Corporation KTH 2008 Tim Walker and Simone Sebben Volvo Car Corporation Page 1 Overview Organisation Influence of Aerodynamics on Passenger Cars Why is aerodynamics important
AUTOMOTIVE COMPUTATIONAL FLUID DYNAMICS SIMULATION OF A CAR USING ANSYS
International Journal of Mechanical Engineering and Technology (IJMET) Volume 7, Issue 2, March-April 2016, pp. 91 104, Article ID: IJMET_07_02_013 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=7&itype=2
132 A. A. HASSAN AND L. N. SANKAR J. AIRCRAFT
VOL. 132 A. A. HASSAN AND L. N. SANKAR J. AIRCRAFT separation JAN.-FEB. 1992 SEPARATION CONTROL 133 H Fig. 1 Physical domain of interest in the present flowfield simulations. 134 A. A. HASSAN AND L. N.
DESIGN OF THE MODERN FAMILY OF HELICOPTER AIRFOILS 51
DESIGN OF THE MODERN FAMILY OF HELICOPTER AIRFOILS Wojciech KANIA, Wieńczysław STALEWSKI, Bogumiła ZWIERZCHOWSKA Institute of Aviation Summary The paper presents results of numerical design and experimental
T E A C H E R S N O T E S
T E A C H E R S N O T E S Focus: Students explore air and its properties. They will also learn about the connection between air pressure and weather, forces that can be used for flight, how these forces
Smart Fixed Wing Aircraft Integrated Technology Demonstrator (SFWA-ITD): New Wing Concepts
Aerodays 2011 conference CleanSky Scenarios for 2020: Conceptual Aircraft Smart Fixed Wing Aircraft Integrated Technology Demonstrator (SFWA-ITD): New Wing Concepts Madrid, 30. March 01. April 2010 J.
Training data requirement for a neural network to predict aerodynamic coefficients
Training data requirement for a neural network to predict aerodynamic coefficients T. Rajkumar and Jorge Bardina SAIC@ NASA Ames Research Center, Moffett Field, California, USA 94 NASA Ames Research Center,
KATnet Key Aerodynamic Technologies for Aircraft Performance Improvement
Fifth Community Aeronautical Days 2006, Vienna, Austria, 19-21 June 2006 Presented by Géza Schrauf Airbus With contributions of Burkhard Gölling and Norman Wood KATnet Key Aerodynamic Technologies for
Design and Characterization of a Small Wind Turbine Model equipped with a Pitching System
Design and Characterization of a Small Wind Turbine Model equipped with a Pitching System In Partial Fulfilment of the Requirements for the degree Master of Science in Engineering Renewable Energy and
I think that a smaller radius of curvature will produce more lift using the Coanda Effect.
The Coanda Conundrum Mackenzie Carter Background My experiment was constructed to test the Coanda effect which occurs when a fluid that is traveling parallel to a nearby surface adheres to that surface.
University of Dayton Graduate School Aerospace Engineering
University of Dayton Graduate School The University of Dayton offers more than 50 disciplinary and cross-disciplinary advanced degree programs, making it easy for you to find a program to meet your needs.
Computational Aerodynamic Analysis on Store Separation from Aircraft using Pylon
International Journal of Engineering Science Invention (IJESI) ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 www.ijesi.org ǁ PP.27-31 Computational Aerodynamic Analysis on Store Separation from Aircraft
FACTORS INFLUENCING THE SPREAD PATTERN FROM SALT SPREADERS
FACTORS INFLUENCING THE SPREAD PATTERN FROM SALT SPREADERS ABSTRACT K. PERSSON, J. S. STRØM & H. TAKAI Engineering Centre Bygholm, Aarhus University, Denmark krister.persson@agrsci.dk T. BRØCHNER Physics
A COMPARISON BETWEEN THE AERODYNAMIC PRESSURE FACTORING AND THE AERODYNAMIC DERIVATIVES FACTORING METHODS FOR THE DOUBLET LATTICE PROGRAM
A COMPARISON BETWEEN THE AERODYNAMIC PRESSURE FACTORING AND THE AERODYNAMIC DERIVATIVES FACTORING METHODS FOR THE DOUBLET LATTICE PROGRAM Paper Reference No. 1-1 by Emil Suciu* esuciu@yahoo.com ABSTRACT
MODULE 11B. PISTON AEROPLANE AERODYNAMICS, STRUCTURES AND SYSTEMS
MODULE 11B. PISTON AEROPLANE AERODYNAMICS, STRUCTURES AND SYSTEMS Note: The scope of this Module should reflect the technology of aeroplanes pertinent to the A2 and B1.2 subcategory. 11.1 Theory of Flight
Program Update June 2015. G500, G600 Program Update 06.15
Program Update June 2015 G500, G600 Program Update 06.15 All-New Gulfstream G500 and G600 All new, best-in-class aircraft that build upon Gulfstream s technology leadership Unmatched high-speed range capability
Lab 1a Wind Tunnel Testing Principles & Lift and Drag Coefficients on an Airfoil
Lab 1a Wind Tunnel Testing Principles & Lift and Drag Coefficients on an Airfoil OBJECTIVES - Calibrate the RPM/wind speed relation of the wind tunnel. - Measure the drag and lift coefficients of an airfoil
Development and optimization of a hybrid passive/active liner for flow duct applications
Development and optimization of a hybrid passive/active liner for flow duct applications 1 INTRODUCTION Design of an acoustic liner effective throughout the entire frequency range inherent in aeronautic
Research Methodology Part III: Thesis Proposal. Dr. Tarek A. Tutunji Mechatronics Engineering Department Philadelphia University - Jordan
Research Methodology Part III: Thesis Proposal Dr. Tarek A. Tutunji Mechatronics Engineering Department Philadelphia University - Jordan Outline Thesis Phases Thesis Proposal Sections Thesis Flow Chart
Identifying Hawks in Flight using the SPASMATIC method:
Identifying Hawks in Flight using the SPASMATIC method: S HAPE (relative sizes and proportions of wings, tail, and head) P ATTERN/PLUMAGE (contrasting patterns of dark and light) A CTIONS (How does the
Computational Fluid Dynamics Investigation of Two Surfboard Fin Configurations.
Computational Fluid Dynamics Investigation of Two Surfboard Fin Configurations. By: Anthony Livanos (10408690) Supervisor: Dr Philippa O Neil Faculty of Engineering University of Western Australia For