FLOW CONTROL APPLIED TO OUTER WING SLAT-EDGE PROBLEM: CFD & EXPERIMENT
|
|
|
- Amos Gallagher
- 5 years ago
- Views:
Transcription
1 FLOW CONTROL APPLIED TO OUTER WING SLAT-EDGE PROBLEM: CFD & EXPERIMENT IAP 30 March 2017 Tel-Aviv University (TAU) IAI: I. Detinis, M. Steinbuch, S. Segal TAU: M. Lagutin & A. Seifert This study is part of the AFLONEXT FP7-EU project Monitored by M. Whalich/Airbus ISCFDC LTD & TAU AerolabTeam Classification-Unclassified
2 Problem: Slat Ends at Wingtip Slat has to be straight Can not extend to the wingtip. Outer part exposed to flow separation. The remedy to the problem is to use Active Flow Control (AFC) on wingtip to eliminate flow separation. Can lead to 2% Fuel savings NO Flow Separation Protected by slats Flow Separation No protection by slats IAP 30 March 2017 Classification-Unclassified 2
3 Current High-lift Systems High Lift Leading Edge & Trailing Edge devices Flaps Increases lift at high Angles of Attack Slats Delays stall at high Angles of Attack IAP 30 March 2017 Classification-Unclassified 3
4 General-Geometry Definition To study the effect of AFC, a generic wing similar to large plane outer wing at high-lift conditions was defined 25º Swept back wing based on airfoil designed by IAI (supercritical) Deflected slat section 20º Deflected flap unprotected wingtip IAP 30 March 2017 Classification-Unclassified 4 4
5 Vortices and Tip Stall AoA=17 AoA=18 AoA=19 The wingtip stalls because vortices shed from slat edge and wingtip merge IAP 30 March 2017 Classification-Unclassified 5 5
![walls (Blowing) 25 Slots@Vj=200[m/sec] P=100KPa AoA=19 ;w/o W/T walls](/docs-images/86/94771259/images/6-5.jpg "(Blowing) 1 Slot@Vj=200[m/sec] P=100KPa No AFC 25slots; Vj=200[m/sec]")
6 Compare Suction to Blowing AoA=19 ;wo W/T walls No AFC AoA=19 ;w/o W/T walls (Suction) 3 Slots@Vj=-40[m/sec] P=50KPa No AFC: The wingtip is separated. 3 slots (suction):there is no wingtip separation. 25 slots(blowing):the wingtip is separated. Single slot(blowing):there is no wingtip separation. 3 slots; suction Vj=-40[m/sec] AoA=19 1 slot; Vj=200[m/sec] AoA=19 ;w/o W/T walls (Blowing) 25 Slots@Vj=200[m/sec] P=100KPa AoA=19 ;w/o W/T walls (Blowing) 1 Slot@Vj=200[m/sec] P=100KPa No AFC 25slots; Vj=200[m/sec] Suction has same effect as blowing at 1/5th magnitude IAP 30 March 2017 Classification-Unclassified 6
7 Indeed Cost of Suction Lower for Same benefit Single slot blowing better than 25 slots blowing 3 Slots suction: Same benefit for less energy (also drag reduction) CFD is a good toll BUT it has to be VALIDATED experimentally 7 IAP 30 March 2017 Classification-Unclassified 7
8 Same Effects on Drag (CFD) Note: The correction due AFC actuation is not included. 25 slots blowing: Low drag reduction at high C. Single slot blowing: Significant drag rise at moderate C. 3 Slots suction: Significant drag reduction at low (AoA=17,18 ) and Significant drag rise at low AoA=19,20. IAP 30 March 2017 Classification-Unclassified 8
9 Experimental Setup TRNLF D airfoil Industrial Geometry Installed VERTICALLY at WT TAU Knapp-Meadow Wind Tunnel The model was Designed, Constructed and Mounted Main TR8 airfoil Profile & TE Flap Leading edge Slat Constant Deflection Wing Tip Semi Circular LE Incidence angles Adjustable: 0-19 Sweep angle settings 0-25 Flap deflections 0-20 Reynolds numbers x 10 6 Overall Near 200 Pressure Taps IAP 30 March 2017 Classification-Unclassified 9
10 Experiment: Lift Increases Wing Tip Integrated Pressure Measuring System. Lift Comparison AoA= AoA= Efficient at AoA 8-13 Best improvement at AoA= Open Slots at 11-3% Improvement Suction of V/U=0.77 at % Improvement AoA= Cl(AoA), Re=700k,WingTipCl,FL20, Slots 1-4 Cl BUGS-TAPED 0.35 BUGS-OPEN-SLOT-1-4 BUGS-V/U= AoA[deg] IAP 30 March 2017 Classification-Unclassified 10
11 Experiment: Vortices Kept Apart! 3D Wake Measurements 7-Holes Probe U[m/s] Vorticity A12, Re700k AFC OFF AFC ON Vorticity, U and Pstat Maps AFC Delays Vortex Merging Cd and Integration Efficient at AoA 8-16 Drastic improvement at AoA=12 Both Reynolds Numbers Vortex separation Drag Reduce Cd/Cd Baseline AFC OFF AFC ON IAP 30 March 2017 Classification-Unclassified 11 AoA[ deg] 1 AFC OFF Re 700 k, AFC ON Re 400 k, AFC ON
12 Flow Visualizations Performed at Re 700k,AoA 12 Oil Test Open Slots U/Uinf=0.77 Infra Red Thermography AFC OFF ON AFC ON OFF Old Separation line Tuft Test AFC OFF AFC ON New Separation line Compatible Results for all the Methods AFC delays separation New Separation line Old Separation line IAP 30 March 2017 Classification-Unclassified 12
13 CFD and Experiment Compared, =12 OFF OFF ON CFD CFD: AoA=12 (No suction) Exp.: AoA=12 (No suction) Exp.: AoA=12 (With Suction) IAP 30 March 2017 Classification-Unclassified 13
14 Conclusions & Recommendations Delaying stall, improving lift and reducing drag at incipient separation stage using slots suction Two orders of magnitude lower power compared to blowing Delays stall and lift drop caused by separation, on the wing tip To be replaced by the TAU developed SaOB Actuator (Patented) Used also for Wind turbines and Trucks A good example for Industry Academia Collaboration 3 Suction Holes Oscillatory Blowing Slots IAP 30 March 2017 Classification-Unclassified 14
Evaluation of High Lift System with Oscillatory Blowing in 2.5D Configuration
Evaluation of High Lift System with Oscillatory Blowing in 2.5D Configuration Cǎtǎlin NAE, Mihai-Victor PRICOP Corresponding author INCAS - National Institute for Aerospace Research Elie Carafoli Bdul
Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft
, July 1-3, 2015, London, U.K. Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft Pooja Pragati, Sudarsan Baskar Abstract This paper provides a practical design of a new concept of massive
ROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool)
Unit D-1: Aerodynamics of 3-D Wings Page 1 of 5 AE301 Aerodynamics I UNIT D: Applied Aerodynamics ROAD MAP... D-1: Aerodynamics of 3-D Wings D-: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics
ADVANCES IN AERODYNAMICS OF WIND TURBINE BLADES
ADVANCES IN AERODYNAMICS OF WIND TURBINE BLADES Herning / October 3 / 2017 By Jesper Madsen Chief Engineer, Aerodynamics & Acoustics WIND ENERGY DENMARK Annual Event 2017 Agenda 1. Aerodynamic design and
EXPERIMENTAL ANALYSIS OF THE CONFLUENT BOUNDARY LAYER BETWEEN A FLAP AND A MAIN ELEMENT WITH SAW-TOOTHED TRAILING EDGE
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL ANALYSIS OF THE CONFLUENT BOUNDARY LAYER BETWEEN A FLAP AND A MAIN ELEMENT WITH SAW-TOOTHED TRAILING EDGE Lemes, Rodrigo Cristian,
AE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability.
Aerodynamics: Introduction Aerodynamics deals with the motion of objects in air. These objects can be airplanes, missiles or road vehicles. The Table below summarizes the aspects of vehicle performance
Experimental and Theoretical Investigation for the Improvement of the Aerodynamic Characteristic of NACA 0012 airfoil
International Journal of Mining, Metallurgy & Mechanical Engineering (IJMMME) Volume 2, Issue 1 (214) ISSN 232 46 (Online) Experimental and Theoretical Investigation for the Improvement of the Aerodynamic
EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT
Chapter-6 EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT 6.1 Introduction The gurney flap (wicker bill) was a small flat tab projecting from the trailing edge of a wing. Typically it
Co-Flow Jet Airfoil for Ultra-High Efficiency and Quiet Aircraft
Co-Flow Jet Airfoil for Ultra-High Efficiency and Quiet Aircraft Patent: US8485476 B2 Dr. Gecheng Zha, President Professor Coflow Jet, LLC PO Box 248661 Coral Gables, FL 33124 gzha@miami.edu http://coflowjet.com
Effect of Co-Flow Jet over an Airfoil: Numerical Approach
Contemporary Engineering Sciences, Vol. 7, 2014, no. 17, 845-851 HIKARI Ltd, www.m-hikari.com http://dx.doi.org/10.12988/ces.2014.4655 Effect of Co-Flow Jet over an Airfoil: Numerical Approach Md. Riajun
Jet Propulsion. Lecture-17. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati
Lecture-17 Prepared under QIP-CD Cell Project Jet Propulsion Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1 Lift: is used to support the weight of
ScienceDirect. Investigation of the aerodynamic characteristics of an aerofoil shaped fuselage UAV model
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 90 (2014 ) 225 231 10th International Conference on Mechanical Engineering, ICME 2013 Investigation of the aerodynamic characteristics
C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory
ROAD MAP... AE301 Aerodynamics I UNIT C: 2-D Airfoils C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory AE301 Aerodynamics I : List of Subjects
EXPERIMENTAL INVESTIGATION OF LIFT & DRAG PERFORMANCE OF NACA0012 WIND TURBINE AEROFOIL
EXPERIMENTAL INVESTIGATION OF LIFT & DRAG PERFORMANCE OF NACA0012 WIND TURBINE AEROFOIL Mr. Sandesh K. Rasal 1, Mr. Rohan R. Katwate 2 1 PG Student, 2 Assistant Professor, DYPSOEA Ambi Talegaon, Heat Power
EXPERIMENTAL ANALYSIS OF FLOW OVER SYMMETRICAL AEROFOIL Mayank Pawar 1, Zankhan Sonara 2 1,2
EXPERIMENTAL ANALYSIS OF FLOW OVER SYMMETRICAL AEROFOIL Mayank Pawar 1, Zankhan Sonara 2 1,2 Assistant Professor,Chandubhai S. Patel Institute of Technology, CHARUSAT, Changa, Gujarat, India Abstract The
EXPERIMENTAL INVESTIGATION OF THE EFFECT OF VARIOUS WINGLET SHAPES ON THE TOTAL PRESSURE DISTRIBUTION BEHIND A WING
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL INVESTIGATION OF THE EFFECT OF VARIOUS WINGLET SHAPES ON THE TOTAL PRESSURE DISTRIBUTION BEHIND A WING Mohammad Reza Soltani, Kaveh
INVESTIGATION OF PRESSURE CONTOURS AND VELOCITY VECTORS OF NACA 0015IN COMPARISON WITH OPTIMIZED NACA 0015 USING GURNEY FLAP
INVESTIGATION OF PRESSURE CONTOURS AND VELOCITY VECTORS OF NACA 0015IN COMPARISON WITH OPTIMIZED NACA 0015 USING GURNEY FLAP 1 ANANTH S SHARMA, 2 SUDHAKAR S, 3 SWATHIJAYAKUMAR, 4 B S ANIL KUMAR 1,2,3,4
Induced Drag Reduction for Modern Aircraft without Increasing the Span of the Wing by Using Winglet
International Journal of Mechanical & Mechatronics Engineering IJMME-IJENS Vol:10 No:03 49 Induced Drag Reduction for Modern Aircraft without Increasing the Span of the Wing by Using Winglet Mohammad Ilias
Incompressible Flow over Airfoils
Road map for Chap. 4 Incompressible Flow over Airfoils Aerodynamics 2015 fall - 1 - < 4.1 Introduction > Incompressible Flow over Airfoils Incompressible flow over airfoils Prandtl (20C 초 ) Airfoil (2D)
THE EFFECT OF LEADING AND TRAILING EDGE PROTUBERANCES ON AEROFOIL PERFORMANCE
HEFAT214 1 th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 14 16 July 214 Orlando, Florida THE EFFECT OF LEADING AND TRAILING EDGE PROTUBERANCES ON AEROFOIL PERFORMANCE
Low Speed Wind Tunnel Wing Performance
Low Speed Wind Tunnel Wing Performance ARO 101L Introduction to Aeronautics Section 01 Group 13 20 November 2015 Aerospace Engineering Department California Polytechnic University, Pomona Team Leader:
Design and CFD Analysis of Parametric Winglets
Design and CFD Analysis Parametric Winglets Mohd Mohiuddin Quraishi*, Mohd Abdul Razakh** & Shivasri Chithaluri*** *Student, Aero Department, Institute Aeronautical Engineering, Hyderabad, Telangana, INDIA.
NUMERICAL INVESTIGATION FOR THE ENHANCEMENT OF THE AERODYNAMIC CHARACTERISTICS OF AN AEROFOIL BY USING A GURNEY FLAP
Geotec., Const. Mat. & Env., ISSN:2186-2990, Japan, DOI: http://dx.doi.org/10.21660/2017.34.2650 NUMERICAL INVESTIGATION FOR THE ENHANCEMENT OF THE AERODYNAMIC CHARACTERISTICS OF AN AEROFOIL BY USING A
Uncontrolled copy not subject to amendment. Principles of Flight
Uncontrolled copy not subject to amendment Principles of Flight Principles of Flight Learning Outcome 3: Know the principles of stalling Principles of Flight Revision Questions What effect does a Trailing
University of Bristol - Explore Bristol Research. Publisher's PDF, also known as Version of record
Liu, X., Azarpeyvand, M., & Joseph, P. (2015). On the acoustic and aerodynamic performance of serrated airfoils. Paper presented at The 22nd International Congress on Sound and Vibration, Florence, France.
Computational Investigation of Airfoils with Miniature Trailing Edge Control Surfaces
AIAA-24-5 Computational Investigation of Airfoils with Miniature Trailing Edge Control Surfaces Hak-Tae Lee, Ilan M. Kroo Stanford University, Stanford, CA 9435 Abstract Miniature trailing edge effectors
Comparing GU & Savier airfoil equipped half canard In S4 wind tunnel (France)
Some notes about Comparing GU & Savier airfoil equipped half canard In S4 wind tunnel (France) Matthieu Scherrer Adapted from Charlie Pujo & Nicolas Gorius work Contents Test conditions 3. S-4 Wind-tunnel.............................................
APPLICATION OF RESEARCH RESULTS AT LM WIND POWER
APPLICATION OF RESEARCH RESULTS AT LM WIND POWER Herning / March 27 / 2014 By Jesper Madsen Chief Engineer Aerodynamics and Acoustics AGENDA 1. EUDP Projects 1. DANAERO MW 2. Optimization of vortex generators
Improved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped Fuselage
International Journal of Scientific & Engineering Research Volume 4, Issue 1, January-213 1 Improved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped
Lecture # 08: Boundary Layer Flows and Drag
AerE 311L & AerE343L Lecture Notes Lecture # 8: Boundary Layer Flows and Drag Dr. Hui H Hu Department of Aerospace Engineering Iowa State University Ames, Iowa 511, U.S.A y AerE343L #4: Hot wire measurements
Reynolds Number Effects on Leading Edge Vortices
Reynolds Number Effects on Leading Edge Vortices Taken From AIAA-2002-2839 Paper Reynolds Numbers Considerations for Supersonic Flight Brenda M. Kulfan 32nd AIAA Fluid Dynamics Conference and Exhibit St.
Aerodynamic investigations on a wing in ground effect
Aerodynamic investigations on a wing in ground effect A summary of NLR activities in the Seabus-Hydaer programme W.B. de Wolf Nationaal Lucht- en Ruimtevaartlaboratorium National Aerospace Laboratory NLR
NAWEA 2015 SYMPOSIUM
Aerodynamics and Aeroacoustics of Spanwise Wavy Trailing Edge Flatback Airfoils: Design Improvement Seung Joon Yang James D. Baeder Alfred Gessow Rotorcraft Center Department of Aerospace Engineering,
Static Extended Trailing Edge for Lift Enhancement: Experimental and Computational Studies
Static Extended Trailing Edge for Lift Enhancement: Experimental and Computational Studies T. Liu, J. Montefort, W. Liou Western Michigan University Kalamazoo, MI 49008 and Q. Shams NASA Langley Research
CFD ANALYSIS OF AIRFOIL SECTIONS
CFD ANALYSIS OF AIRFOIL SECTIONS Vinayak Chumbre 1, T. Rushikesh 2, Sagar Umatar 3, Shirish M. Kerur 4 1,2,3 Student, Jain College of Engineering, Belagavi, Karnataka, INDIA 4Professor, Dept. of Mechanical
WING PROFILE WITH VARIABLE FLAP
WING PROFILE WITH VARIABLE FLAP March 2009 INTRODUCTION Flaps are something that can be found on a majority of aeroplanes. That they fill an important purpose in affecting the aircraft s performance is
Computational Analysis of Blunt Trailing Edge NACA 0012 Airfoil
Computational Analysis of Blunt Trailing Edge NACA 2 Airfoil Anusha K Department of Aerospace Engineering Madras Institute of Technology, India anusugan7@gmail.com Abstract Blunt trailing edge airfoil
EXPERIMENTAL AND NUMERICAL STUDY OF A TWO- ELEMENT WING WITH GURNEY FLAP
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL AND NUMERICAL STUDY OF A TWO- ELEMENT WING WITH GURNEY FLAP F.M. Catalano PhD.( catalano@sc.usp.br ) *, G. L. Brand * * Aerodynamic
CFD Analysis of Supercritical Airfoil with Different Camber
CFD Analysis of Supercritical Airfoil with Different Camber S.Manikandan 1, R.G.Bhuvana 2, Sowmya.A.Srinivasan 3 Assistant prof, Department of Aeronautical Engineering, Jeppiaar Engineering College, Chennai,
Reduction of Skin Friction Drag in Wings by Employing Riblets
Reduction of Skin Friction Drag in Wings by Employing Riblets Kousik Kumaar. R 1 Assistant Professor Department of Aeronautical Engineering Nehru Institute of Engineering and Technology Coimbatore, India
Aerodynamic investigation of Winglets on Wind Turbine Blades using CFD
Risø-R-1543(EN) Aerodynamic investigation of Winglets on Wind Turbine Blades using CFD Jeppe Johansen and Niels N. Sørensen Risø National Laboratory Roskilde Denmark February 26 Author: Jeppe Johansen
The Effect of Slot Configuration on Active Flow Control Performance of Swept Wings at. Low Reynolds Numbers. Thesis
The Effect of Slot Configuration on Active Flow Control Performance of Swept Wings at Low Reynolds Numbers Thesis Presented in Partial Fulfillment of the Requirements for Graduation with Honors Research
8d. Aquatic & Aerial Locomotion. Zoology 430: Animal Physiology
8d. Aquatic & Aerial Locomotion 1 Newton s Laws of Motion First Law of Motion The law of inertia: a body retains its state of rest or motion unless acted on by an external force. Second Law of Motion F
ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT
ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT P.Sethunathan 1, M.Niventhran 2, V.Siva 2, R.Sadhan Kumar 2 1 Asst.Professor, Department of Aeronautical Engineering,
Air Craft Winglet Design and Performance: Cant Angle Effect
Journal of Robotics and Mechanical Engineering Research Air Craft Winglet Design and Performance: Cant Angle Effect Eslam Said Abdelghany 1, Essam E Khalil 2*, Osama E Abdellatif 3 and Gamal elhariry 4
Lab 4: Pressure Gradients over a Wing
2009 Lab 4: Pressure Gradients over a Wing Innovative Scientific Solutions Inc. 2766 Indian Ripple Road Dayton, OH 45440 (937)-429-4980 Lab 4: Pressure Gradients over a Wing Introduction: Like the previous
CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS
www.mechieprojects.com CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS PRESENTATION OUTLINE AIM INTRODUCTION LITERATURE SURVEY CFD ANALYSIS OF AEROFOIL RESULTS CONCLUSIONS www.mechieprojects.com
No Description Direction Source 1. Thrust
AERODYNAMICS FORCES 1. WORKING TOGETHER Actually Lift Force is not the only force working on the aircraft, during aircraft moving through the air. There are several aerodynamics forces working together
Exploration Series. AIRPLANE Interactive Physics Simulation Page 01
AIRPLANE ------- Interactive Physics Simulation ------- Page 01 What makes an airplane "stall"? An airplane changes its state of motion thanks to an imbalance in the four main forces acting on it: lift,
NUMERICAL INVESTIGATION OF FLOW OVER MULTI- ELEMENT AIRFOILS WITH LIFT-ENHANCING TABS
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES NUMERICAL INVESTIGATION OF FLOW OVER MULTI- ELEMENT AIRFOILS WITH LIFT-ENHANCING TABS Zhenhui Zhang, Dong Li National Key Laboratory of Science
Homework Exercise to prepare for Class #2.
Homework Exercise to prepare for Class #2. Answer these on notebook paper then correct or improve your answers (using another color) by referring to the answer sheet. 1. Identify the major components depicted
Avai 193 Fall 2016 Laboratory Greensheet
Avai 193 Fall 2016 Laboratory Greensheet Lab Report 1 Title: Instrumentation Test Technique Research Process: Break into groups of 4 people. These groups will be the same for all of the experiments performed
FLOW SIMULATION OF AN SST CONFIGURATION AT LOW-SPEED AND HIGH-LIFT CONDITIONS
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FLOW SIMULATION OF AN SST CONFIGURATION AT LOW-SPEED AND HIGH-LIFT CONDITIONS Zhong Lei, Dong-Youn Kwak Supersonic Transport Team, Japan Aerospace
2-D Computational Analysis of a Vertical Axis Wind Turbine Airfoil
2-D Computational Analysis of a Vertical Axis Wind Turbine Airfoil Akshay Basavaraj1 Student, Department of Aerospace Engineering, Amrita School of Engineering, Coimbatore 641 112, India1 Abstract: This
Part III: Airfoil Data. Philippe Giguère
Part III: Airfoil Data Philippe Giguère Former Graduate Research Assistant (now with GE Wind Energy) Department of Aerospace Engineering University of Illinois at Urbana-Champaign Steady-State Aerodynamics
The Metric Glider. By Steven A. Bachmeyer. Aerospace Technology Education Series
The Metric Glider By Steven A. Bachmeyer Aerospace Technology Education Series 10002 Photographs and Illustrations The author wishes to acknowledge the following individuals and organizations for the photographs
Wind tunnel effects on wingtip vortices
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 2010, Orlando, Florida AIAA 2010-325 Wind tunnel effects on wingtip vortices Xin Huang 1, Hirofumi
Lecture # 08: Boundary Layer Flows and Controls
AerE 344 Lecture Notes Lecture # 8: Boundary Layer Flows and Controls Dr. Hui Hu Department of Aerospace Engineering Iowa State University Ames, Iowa 511, U.S.A Flow Separation on an Airfoil Quantification
Design Analysis and Optimization Of Wing With Variable Camber Continuous Trailing Edge Flap
Design Analysis and Optimization Of Wing With Variable Camber Continuous Trailing Edge Flap G.Anandhi a,k.karuppasamy b a P.G Scholar Master of Aeronautical Engineering Regional Centre of Anna University
Investigation and Comparison of Airfoils
AENG 360 Aerodynamics Investigation and Comparison of Airfoils Rocie Benavent Chelseyann Bipat Brandon Gilyard Julian Marcon New York Institute of Technology Fall 2013 2 Executive Summary Airfoil design
THE COLLEGE OF AERONAUTICS CRANFIELD
THE COLLEGE OF AERONAUTICS CRANFIELD AERODYNAMIC CHARACTERISTICS OF A 40 SWEPT BACK WING OF ASPECT RATIO 4.5 by P. S. BARNA NOTE NO. 65 MAY, 1957 CRANFIELD A preliminary report on the aerodynamic characteristics
Aerodynamic Analysis of a Symmetric Aerofoil
214 IJEDR Volume 2, Issue 4 ISSN: 2321-9939 Aerodynamic Analysis of a Symmetric Aerofoil Narayan U Rathod Department of Mechanical Engineering, BMS college of Engineering, Bangalore, India Abstract - The
WINGLET CANT AND SWEEP ANGLES EFFECT ON AIRCRAFT WING PERFORMANCE
Proceedings of the 17 th Int. AMME Conference, 19-21 April, 216 258 Military Technical College Kobry El-Kobbah, Cairo, Egypt. 17 th International Conference on Applied Mechanics and Mechanical Engineering.
Development of high-lift laminar wing using steady active flow control
Graduate Theses and Dissertations Iowa State University Capstones, Theses and Dissertations 2013 Development of high-lift laminar wing using steady active flow control Patrick Clayton Iowa State University
Effects of Planform Geometry and Pivot Axis Location on the Aerodynamics of Pitching Low Aspect Ratio Wings
Fluid Dynamics and Co-located Conferences June 4-7,, San Diego, CA 4rd Fluid Dynamics Conference AIAA -99 Effects of Planform Geometry and Pivot Axis Location on the Aerodynamics of Pitching Low Aspect
Flow Over Bodies: Drag and Lift
Fluid Mechanics (0905241) Flow Over Bodies: Drag and Lift Dr.-Eng. Zayed dal-hamamre 1 Content Overview Drag and Lift Flow Past Objects Boundary Layers Laminar Boundary Layers Transitional and Turbulent
A comparison of NACA 0012 and NACA 0021 self-noise at low Reynolds number
A comparison of NACA 12 and NACA 21 self-noise at low Reynolds number A. Laratro, M. Arjomandi, B. Cazzolato, R. Kelso Abstract The self-noise of NACA 12 and NACA 21 airfoils are recorded at a Reynolds
TRAILING EDGE TREATMENT TO ENHANCE HIGH LIFT SYSTEM PERFORMANCE
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES TRAILING EDGE TREATMENT TO ENHANCE HIGH LIFT SYSTEM PERFORMANCE Catalano F.M.*, Ceròn E.D.* Greco P.C. * Laboratory of Aerodynamics EESC-USP Brazil
Incompressible Potential Flow. Panel Methods (3)
Incompressible Potential Flow Panel Methods (3) Outline Some Potential Theory Derivation of the Integral Equation for the Potential Classic Panel Method Program PANEL Subsonic Airfoil Aerodynamics Issues
INTERFERENCE EFFECT AND FLOW PATTERN OF FOUR BIPLANE CONFIGURATIONS USING NACA 0024 PROFILE
Proceedings of the International Conference on Mechanical Engineering 211 (ICME211) 18-2 December 211, Dhaka, Bangladesh ICME11-FL-1 INTERFERENCE EFFECT AND FLOW PATTERN OF FOUR BIPLANE CONFIGURATIONS
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK SUPREETH NARASIMHAMURTHY GRADUATE STUDENT 1327291 Table of Contents 1) Introduction...1 2) Methodology.3 3) Results...5
CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS
Colloquium FLUID DYNAMICS 2008 Institute of Thermomechanics AS CR, v.v.i., Prague, October 22-24, 2008 p.1 CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS Vladimír Horák 1, Dalibor
AERODYNAMIC ANALYSIS OF MULTI-WINGLETS FOR LOW SPEED AIRCRAFT
AERODYNAMIC ANALYSIS OF MULTI-WINGLETS FOR LOW SPEED AIRCRAFT Cosin, R., Catalano, F.M., Correa, L.G.N., Entz, R.M.U. Engineering School of São Carlos - University of São Paulo Keywords: multi-winglets,
Design And Performance Analysis Of Bump Surface In An Airfoil
ISSN: 2278 0211 (Online) Design And Performance Analysis Of Bump Surface In An Airfoil Nithya S. School Of Aeronautical Sciences, Hindustan University, India G. Dineshkumar School Of Aeronautical Sciences,
Job Sheet 1 Blade Aerodynamics
Job Sheet 1 Blade Aerodynamics The rotor is the most important part of a wind turbine. It is through the rotor that the energy of the wind is converted into mechanical energy, which turns the main shaft
The Influence of Battle Damage on the Aerodynamic Characteristics of a Model of an Aircraft
Proceedings of the 26 WSEAS/IASME International Conference on Fluid Mechanics, Miami, Florida, USA, January 18-2, 26 (pp7-76) The Influence of Battle on the Aerodynamic Characteristics of a Model of an
CIRCULATION CONTROLLED AIRFOIL ANALYSIS THROUGH 360 DEGREES ANGLE OF ATTACK
Proceedings of the ASME 2009 3rd International Conference of Proceedings Energy Sustainability of ES2009 Energy Sustainability ES2009 July July 19-23, 2009, 2009, San San Francisco, California, USA ES2009-90341
PIV Analysis of a Delta Wing Flow with or without LEX(Leading Edge Extension)
PIV Analysis of a Delta Wing Flow with or without LEX(Leading Edge Extension) by Young-Ho LEE (1) (Korea Maritime University), Myong-Hwan SOHN (2) (Korea Air Force Academy) Hyun LEE (3), Jung-Hwan KIM
STUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS
ICAS 2000 CONGRESS STUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS Kenichi RINOIE Department of Aeronautics and Astronautics, University of Tokyo, Tokyo, 113-8656, JAPAN Keywords: vortex flap,
CFD study of section characteristics of Formula Mazda race car wings
Mathematical and Computer Modelling 43 (2006) 1275 1287 www.elsevier.com/locate/mcm CFD study of section characteristics of Formula Mazda race car wings W. Kieffer a, S. Moujaes b,, N. Armbya b a MSME
et al. [25], Noack et al. [26] for circular cylinder flows, Van Oudheusden [27] for square cylinder and Durgesh [28] for a flat plate model. The first two modes appear as phase-shifted versions of each
Basic Fluid Mechanics
Basic Fluid Mechanics Chapter 7B: Forces on Submerged Bodies 7/26/2018 C7B: Forces on Submerged Bodies 1 Forces on Submerged Bodies Lift and Drag are forces exerted on an immersed body by the surrounding
PASSIVE FLOW SEPARATION CONTROL BY STATIC EXTENDED TRAILING EDGE
Proceedings of the International Conference on Mechanical Engineering and Renewable Energy 25 (ICMERE25) 26 29 November, 25, Chittagong, Bangladesh ICMERE25-PI-232 PASSIVE FLOW SEPARATION CONTROL BY STATIC
ANALYSIS OF TRANSONIC FLOW OVER SUPERCRITICAL AIRFOIL USING CFD FOR GAS TURBINE BLADES
ANALYSIS OF TRANSONIC FLOW OVER SUPERCRITICAL AIRFOIL USING CFD FOR GAS TURBINE BLADES Kushal Gandecha 1 and Kalpit P. Kaurase 2 Abstract 1 Department of Mechanical Engineering, School of Engineering and
14th Applied Aerodynamics Conference June 17-20, 1996 / New Orleans, LA
AIAA 96-2386 Study of Semi-Span Model Testing Techniques G. M. Gatlin and R. J. McGhee NASA Langley Research Center Hampton, VA 23681-1 14th Applied Aerodynamics Conference June 17-2, 1996 / New Orleans,
Aerodynamics of Winglet: A Computational Fluid Dynamics Study Using Fluent
Aerodynamics of : A Computational Fluid Dynamics Study Using Fluent Rohit Jain 1, Mr. Sandeep Jain, Mr. Lokesh Bajpai 1PG Student, Associate Professor, Professor & Head 1 Mechanical Engineering Department
Aerodynamic Design, Fabrication and Testing of Wind Turbine Rotor Blades
Aerodynamic Design, Fabrication and Testing of Wind Turbine Rotor Blades T.Mahendrapandian Department of Mechanical Engineering P.G. Student, Regional Centre of Anna University, Tirunelveli, Tamilnadu,
Design & Analysis of Natural Laminar Flow Supercritical Aerofoil for Increasing L/D Ratio Using Gurney Flap
Design & Analysis of Natural Laminar Flow Supercritical Aerofoil for Increasing L/D Ratio Using Gurney Flap U.Praveenkumar 1, E.T.Chullai 2 M.Tech Student, School of Aeronautical Science, Hindustan University,
Improvement of an Artificial Stall Warning System for Sailplanes
Improvement of an Artificial Stall Warning System for Sailplanes Loek M. M. Boermans and Bart Berendsen Delft University of Technology, Faculty of Aerospace Engineering P.O.Box 5058, 2600 GB Delft, The
The Effect of Blade Thickness and Angle of Attack on Broadband Fan Noise
The Effect of Blade Thickness and Angle of Attack on Broadband Fan Noise Stewart Glegg Florida Atlantic University and William Devenport Virginia Tech Work Supported by ONR, Prog. Manager: Dr. Ron Joslin
Experimental Investigation of Dynamic Load Control Strategies using Active Microflaps on Wind Turbine Blades.
170 Experimental Investigation of Dynamic Load Control Strategies using Active Microflaps on Wind Turbine Blades. Authors & organisations F= First author P= Presenter Oliver Eisele oliver.eisele@fd.tu-berlin.de(1)
Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. Kanin Homsrivaranon
Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil By Kanin Homsrivaranon Submitted to the graduate program in Aerospace Engineering and the Graduate Faculty of the University
Aerodynamic Analyses of Horizontal Axis Wind Turbine By Different Blade Airfoil Using Computer Program
ISSN : 2250-3021 Aerodynamic Analyses of Horizontal Axis Wind Turbine By Different Blade Airfoil Using Computer Program ARVIND SINGH RATHORE 1, SIRAJ AHMED 2 1 (Department of Mechanical Engineering Maulana
AERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING
ICAS 2002 CONGRESS AERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING Yoshiaki NAKAMURA (nakamura@nuae.nagoya-u.ac.jp) Takafumi YAMADA (yamada@nuae.nagoya-u.ac.jp) Department of Aerospace Engineering,
Chapter 5 Wing design - selection of wing parameters - 4 Lecture 22 Topics
Chapter 5 Wing design - selection of wing parameters - Lecture Topics 5.3.9 Ailerons 5.3.0 Other aspects of wing design Example 5. 5.3.9 Ailerons The main purpose of the ailerons is to create rolling moment
Investigations on axial compressor cascades with aspiration on blades and hub
Investigations on axial compressor cascades with aspiration hub Thierry Obrecht Michel Dumas Elia Colombo - Cécile Deslot Snecma (Groupe Safran) Peter Ott Villaroche, France Laboratoire de Thermique Appliquée
PNEUMATIC CHANNEL WING POWERED-LIFT ADVANCED SUPER- STOL AIRCRAFT
1st Flow Control Conference 24-26 June 2002, St. Louis, Missouri AIAA 2002-3275 AIAA 2002-3275 PNEUMATIC CHANNEL WING POWERED-LIFT ADVANCED SUPER- STOL AIRCRAFT Robert J. Englar* Georgia Tech Research
Subsonic wind tunnel models
aerodynamics AF1300a to AF1300l A selection of optional models for use with TecQuipment s Subsonic Wind Tunnel (AF1300) Dimpled Sphere Drag Model (from AF1300j) shown inside the TecQuipment AF1300 Wind
Numerical and Experimental Investigations of Lift and Drag Performances of NACA 0015 Wind Turbine Airfoil
International Journal of Materials, Mechanics and Manufacturing, Vol. 3, No., February 2 Numerical and Experimental Investigations of Lift and Drag Performances of NACA Wind Turbine Airfoil İzzet Şahin
THE CONCEPT OF HIGH-LIFT, MILD STALL WING
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES THE CONCEPT OF HIGH-LIFT, MILD STALL WING Alexander Nagel and Misha Shepshelovich Engineering Center, Israel Aircraft Industries Keywords: airfoils,