DOCSLIB.ORG

Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 12-2005 Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators Charles Roy McConnell University of Tennessee, Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Aerospace Engineering Commons Recommended Citation McConnell, Charles Roy, "Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators. " Master's Thesis, University of Tennessee, 2005. https://trace.tennessee.edu/utk_gradthes/4590 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Charles Roy McConnell entitled "Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the equirr ements for the degree of Master of Science, with a major in Aerospace Engineering. Robert Bond, Major Professor We have read this thesis and recommend its acceptance: Majid Keyhani, M. W. Milligan Accepted for the Council: Carolyn R. Hodges Vice Provost and Dean of the Graduate School (Original signatures are on file with official studentecor r ds.) To the Graduate Council I am submitting herewith a thesis written by Charles Roy McConnell Jr entitled "Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators." I have examined the final paper copy of this thesis forform and content and recommend that it be accepted in partial fulfillmentof the requirements forthe degree of Master of Science, with a major in Aerospace Engineering. 4��g/Robert Bond,MajorProfessor We have read this thesis and recommend its acceptance: Acceptance forthe Council: Experimental Aerodynamic Analysis of a Wing-Flap System with Delta Vortex Generators A Thesis Presented for the Master of Science Degree The University of Tennessee, Knoxville Charles Roy McConnell Jr December 2005 ACKNOWLEDGEMENTS I would like to express volumes of thanks to all those involved in helping me through the process of completing my thesis research. I would like to express my deepest gratitude to Dr. Bond who has always been there to consult with on troubling issues and to just sit and have a chat with. He has been instrumental in helping to fund this research and his willingness to assist me was more than I could have expected. He has been a valued mentor, teacher, motivator, and friend; I am very thankful forhaving had the opportunity to work with him on this research. To my committee members, Dr.'s Milligan and Keyhani, I am thankful that you have been able to be a part of this research and I am even more thankful of the influences that you have had on my education. If not for the educational impressions made upon me by you, I would not be able to consider my experiences at the University of Tennessee nearly as valuable as they have been. I would also like to thank the Department of Mechanical, Aerospace and Biomedical Engineering at the University of Tennessee; the faculty and staffhave always been there to assist me. There have been a handful of educators in my life that have had a memorable influence on my desire to learnand on my commitment to achieve. Most importantly is Dr. Eric Klumpe, if not forhim there is no doubt that I would not be where I am today in obtaining a career as an Aerospace Engineer. I would also like to thank my wife, Jennifer. Her grace has always amazed me and her compassion for others influences me to recognize my own faults and want to be a 11 better person. Her support in my pursuit of this degree has been unwavering and she has been my motivation when I've been overwhelmed by the graduate school experience. I have been blessed by the gift of her and I would not be where I am today if it were not for that blessing. I would also like to thank my family, I appreciate their encouragement and pride in my pursuit of this degree. I am thankful that there has always been a place for me in the family business and even more thankfulthat they have been so supportive of my desire to leave that life and become an engineer. lll ABSTRACT Experimental Aerodynamic Analysis of A Wing-Flap System with Delta Vortex Generators By Charles McConnell Jr The principle idea upon which the use of vortex generators (VGs) is based has been to control flow separation. The characteristic ofVGs has been used to improve lift and alter the stall characteristics of aircraft and has been a relatively common practice for many years. Due to the seemingly limitless range ofVG geometries and arrangements, which are largely dependant upon the desired aerodynamic performance, there has been a broad investigation into VG application. The purpose of this experimental investigation has been to collect data to be used to establish the effects ofvarious delta shaped vortex generators (delta-VGs) geometries and locations for comparison with a baseline model. The data for this research were collected using the University of Tennessee subsonic wind tunnel and were used to produce aerodynamic information including coefficients for lift, drag and pitching moment. In this research program it was found that delta-VGs mounted along the flap­ hinge line produced little effect on lift. It was believed that flowseparation was either induced by the delta-VGs or that separation simply occurred beforethe delta-VGs could aide in the flow characteristics on the model. Testing with the delta-VGs nearthe leading edge of the model produced significant aerodynamic benefit regardless of the delta-VG arrangement. Continued experiments on some of the more beneficialarrangements lV identifiedthat the length and the spacing between the delta-VGs produced results that could improve the maximum lift coefficient, the angle of attack at which it occurred and improved the lift to drag ratio. In the case of a¾" length delta-VG with a 2" spacing and a 60° sweep angle, improvements by as much as 57% fromthe baseline where observed in C1max· The separation region forthis configurationwas also delayed by 4 °. These experiments also revealed that decreasing the spacing between delta-VGs increased the magnitude of the lift to drag ratio and in some cases extended the angle at which the maximum lift to drag ratio occurred. V TABLE OF CONTENTS CHAPTER 1: INTRODUCTION.......................................................................... 1 CHAPTER 2: LITERATURE REVIEW ............................................................... 3 CHAPTER 3: EXPERIMENTAL APPARATUS.................................................. 7 3.1 UTK Subsonic Wind Tunnel ............................................................. 7 3.2 Wind Tunnel Instrumentation and Equipment ....................... , ........... 7 3.3 Calibration of Test Equipment .......................................................... 9 3.4 Two Dimensional Wind Tunnel Model . .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. 11 CHAPTER 4: EXPERIMENTAL PROCEDURE................................................ 13 4.1 Experimental Test Procedure.......................................................... 13 4.2 Experimental Data Acquisition Procedure....................................... 14 4.3 Experimental Determination of Aerodynamic Coefficients.............. 15 4.4 Experimental Placement of Vortex Generators................................ 15 4.5 Error Estimation for Experimental Data.......................................... 16 CHAPTER 5: RESULTS ANDDISCUSSION ................................................... 20 5.1 Baseline Model Data....................................................................... 20 5.2 Length Comparison of Vortex Generators at Flap-Hinge Line........ 22 5.3 Spacing Comparison of Vortex Generators at Flap-Hinge Line ...... 22 5.4 Additional Geometries of Vortex Generators at Flap Hinge Line...... 23 5.5 Surface Comparison of Leading Edge Vortex Generators............... 23 5.6 Length Comparison of Leading Edge Vortex Generators................ 25 5.7 Spacing Comparison of Leading Edge Vortex Generators .............. 26 Vl CHAPTER 6: CONCLUSIONS........................................................................... 28 LIST OF REFERENCES ...................................................................................... 31 APPENDIX.......................................................................................................... 33 VITA .................................................................................................................. 107 vu LIST OF TABLES Table Page 4.1.1 Experimental Test Matrix ......................................................................... 34 4.5.1 Calculation of Error in Lift....................................................................... 34 4.5.2 Calculation of Error in Drag..................................................................... 34 4.5.3 Calculation of Error in Pitching Moment.................................................. 35 4.5.4 Error in Dynamic Pressure, Effect on Lift................................................. 35 4.5.5 Error in Dynamic Pressure, Effect on Drag...............................................
Load more

Recommended publications
  • Program Monitors
    ALLEVIATION OF FUSELAGE FORM DRAG USING VORTEX FLOWS DOE/CE/15277--T1 Final Report on work performed under TI89 004158 U.S. Department of Energy Grant DE-FG01-86CE15277 15 September 1987 DISCLAIMER DR. A. Wortman This report was prepared as an account of work sponsored by an agency of the United States Government. Neither the United States Government nor any agency thereof, nor any of their employees, makes any warranty, express or implied, or assumes any legal liability or responsi- bility for the accuracy, completeness. or usefulness of any information, apparatus, product, or . process disclosed, or represents that its use would not infringe privately owned rights. Refer- ence herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise does not necessarily constitute or imply its endorsement, recom- mendation, or favoring by the United States Government or any agency thereof. The views and opinions of authors expressed herein do not necessarily state or reflect those of the United States Government or any agency thereof. ISTAR INC. 406 Aka Avenue Santa Monica, CA 90402 (213) 394-7332 PROGRAM MONITORS: _* T. Levinson D. Mello DISCLAIMER Portions of this document may be illegible electronic image products. Images are produced from the best available original document. FOREWORD AND ACKNOWLEDGEMENTS The concept of employing discrete large vortices, to develop favorable cross-flow and to energize the boundary layer in the aft regions of transport aircraft fuselages, was first proposed by the author almost 10 years ago as an apparently original approach to the reduction of fuselage drag. A series of feasibility demonstration proposals, starting with the 1981 USAF DESAT program was submitted to various U.S.
    [Show full text]
  • NASA Contractor Report 165749
    NASA Contractor Report 165749 (IASA-Ci!- 165749) SUUSQNli PIfCti- UP Etb 1-30137 ALLEVIATICN ON A 7U CEG DELTA hXh2 (Viqyau Rl~ssdrch Associates, Inc,) LO p HC A02/64F 801 CSCL 1)1C (iluclas Gj/OU &7267 SUBSONIC PITCH-UP ALLEVIATION ON A 74 DEG. DELTA WING Dhanvada W. Raa9iI: and Thomas D, Johnson, Jr. VIGYAN RESEARCH ASSOCIATES, INC . 28 Research Drive Hampton, Virgini a 23666 Contract NAS1-16259 July 1981 National Aeronautis and Space Administration Langley Reamrch Center Hampton,Virginia 23665 SUBSONIC PITCH-UP ALLEVIATION ON A 74-REG, DELTA WING Rhanvada M, Rao Vigyan Research Associates, Inc. and Thomas 0. Johnson, Jr. Kentron International, Inc. tiampton Technical Center SUMMARY Fixed leading-edge devices were investigated on a 74-deg. delta wing model for alleviating the low speed pitch-up and longi- tudinal instability following the onset of leading edge separation. Wind tunnel tests showed Pylon Vortex Generators to be highly effective, compared to the leading-edge fences and slots also investigated. The best Pylon Vortex Generator arrangement raised the pitch-up angle of attack from 8 deg. on the basic wing to 28 deg. , with negl igi bl e subsonic drag penalty . INTRODUCTION A review of research on the low-speed aerodynamics of highly swept wing configurations representative of supersonic-crui se aircraft designs indicates that a problem commonly observed is the so-cal led 'pitch-up' , i.e., a discontinuous nose-up change in the pitching moment uith increasing angle of attack. Pitch-up is caused by the onset of separation in the wing tip regions while the flow inboard is still attached, and has been of sufficient concern to dictate a comproniize in the optimum supersonic-crui se planform shape in order to have accept- able low-speed flight characteristics.
    [Show full text]
  • The Power for Flight: NASA's Contributions To
    The Power Power The forFlight NASA’s Contributions to Aircraft Propulsion for for Flight Jeremy R. Kinney ThePower for NASA’s Contributions to Aircraft Propulsion Flight Jeremy R. Kinney Library of Congress Cataloging-in-Publication Data Names: Kinney, Jeremy R., author. Title: The power for flight : NASA’s contributions to aircraft propulsion / Jeremy R. Kinney. Description: Washington, DC : National Aeronautics and Space Administration, [2017] | Includes bibliographical references and index. Identifiers: LCCN 2017027182 (print) | LCCN 2017028761 (ebook) | ISBN 9781626830387 (Epub) | ISBN 9781626830370 (hardcover) ) | ISBN 9781626830394 (softcover) Subjects: LCSH: United States. National Aeronautics and Space Administration– Research–History. | Airplanes–Jet propulsion–Research–United States– History. | Airplanes–Motors–Research–United States–History. Classification: LCC TL521.312 (ebook) | LCC TL521.312 .K47 2017 (print) | DDC 629.134/35072073–dc23 LC record available at https://lccn.loc.gov/2017027182 Copyright © 2017 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks National Aeronautics and Space Administration Washington, DC Table of Contents Dedication v Acknowledgments vi Foreword vii Chapter 1: The NACA and Aircraft Propulsion, 1915–1958.................................1 Chapter 2: NASA Gets to Work, 1958–1975 ..................................................... 49 Chapter 3: The Shift Toward Commercial Aviation, 1966–1975 ...................... 73 Chapter 4: The Quest for Propulsive Efficiency, 1976–1989 ......................... 103 Chapter 5: Propulsion Control Enters the Computer Era, 1976–1998 ........... 139 Chapter 6: Transiting to a New Century, 1990–2008 ....................................
    [Show full text]
  • Subsonic and Transonic Flutter and Flow Investigations of the T-Tail of a Large Multijet Cargo Airplane
    1 -1.0 8% NASA TECHNICAL NOTE NASA TN D-4316 -c - SUBSONIC AND TRANSONIC FLUTTER I AND FLOW INVESTIGATIONS OF THE T-TAIL OF A LARGE MULTIJET CARGO AIRPLANE Langley Reseurch Center Ldngley Station, Humpton, Vu. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. FEBRUARY 1968 i i 1 t i r SUBSONIC AND TRANSONIC FLUTTER AND FLOW INVESTIGATIONS OF THE T-TAIL OF A LARGE MULTIJET CARGO AIRPLANE By Maynard C. Sandford, Charles L. Ruhlin, and E. Carson Yates, Jr. Langley Research Center Langley Station, Hampton, Va. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federol Scientific and Technical Information Springfield, Virginia 22151 - CFSTl price $3.00 SUBSONIC AND TRANSONIC FLUTTER AND FLOW INVESTIGATIONS OF THE T-TAIL OF A LARGE MULTIJET CARGO AIRPLANE By Maynard C. Sandford, Charles L. Ruhlin, and E. Carson Yates, Jr. Langley Research Center . - SUMMARY Flutter and flow studies of the T-tail of a large multijet cargo airplane have been conducted in the Langley transonic dynamics tunnel at Mach numbers up to 1.08. The tail and aft fuselage of the model employed were geometrically, dynamically, and elastically scaled, whereas only the mass and stiffness characteristics of the forward fuselage, wings, and nacelles were simulated. The flutter studies included variations in fin-spar stiffness, stabilizer-pitch-actuator stiffness, rotational stiffnesses of elevators and rudder, as well as small variations in stabilizer incidence angle. Flow studies were initiated to reduce areas of separated flow in the vicinity of the fin-stabilizer juncture and included the use of vortex generators and fences, as well as modifications to the bullet-fairing shape.
    [Show full text]
  • Vortex Generators: Band-Aids Or Magic?
    Twin Topics Twin Topics is a monthly column devoted to the operation, maintenance, and ownership of Cessna 300- and 400- series piston twins. It is edited by Mike Busch, CPA’s staff twin expert and the lead instructor in CPA’s twin courses. Mike is a regular contributor to CPA Magazine, as well as editor-in-chief of AVweb, the Internet’s aviation magazine and news service (http://www.avweb.com). He also is the owner of a pristine 1979 Cessna T310R which he maintains almost entirely himself. Vortex Generators: Band-Aids or Magic? A recent visit to Boundary Layer Research revealed that there’s a lot more to those little wing and tail bumps than meets the eye, and that they’re not just for twins anymore! by Mike Busch <[email protected]> obody’s ever accused seemed like the only one on the engineers would routinely scoff me of being an early- road that didn’t have one! at the VGs on Boeing jets and Nadopter when it comes Even the most died-in-the- brag, “see, we don’t need those to aviation. I’m unabashedly wool skeptics were unanimous things because we got our aero- skeptical about aeronautical in- that vortex generators are a ma- dynamics right in the first novations until they’ve been jor advance in piston twin safety, place.” proven in the field for years. lowering Vmc by ten knots or so The idea of using VGs to When Mobil AV-1 was being to the point that it is no longer a improve the low-speed perform- touted as the greatest thing since factor (because it is below stall ance of general aviation aircraft sliced bread, I stuck with my speed).
    [Show full text]
  • Measurements on a Vertical Tail with Vane Vortex Generators
    Deutscher Luft- und Raumfahrtkongress 2017 DocumentID: 450111 MEASUREMENTS ON A VERTICAL TAIL WITH VANE VORTEX GENERATORS V. M. Singh, P. Scholz Institute of Fluid Mechanics, TU Braunschweig, Braunschweig, D-38108, Germany Abstract This contribution presents the investigation of a passive method of boundary layer separation control on a swept and tapered vertical tail plane with a deflected rudder. The primary objective was the increase of the total side force coefficient. For that, an array of co-rotating vane vortex generators was placed close to the rudder knee to maintain an attached flow, which consequently led to an increase of the side force coefficient. The second objective was a parameter sensitivity study, which covered a large scope of different vane vortex generator parameters: size, shape, angle of attack, position and separation. Experiments were performed in a low-speed wind tunnel. The results show the ability of vane vortex generators to increase the side force coefficient for a large range of yaw angles. The maximal increase of side force coefficient was about 14 %. However, the influence of the vane vortex generators on the stall of the vertical tail plane was limited. Nevertheless, in a range of yaw angles, an increase of the lift to drag ratio of about 30 % was obtained. The effect was found to be sensitive for the angle of attack, chordwise position, size and geometry of a vortex generator, whereas parameters such as spanwise extension and separation were less sensitive to parameter change. NOMENCLATURE maneuvers. Although the main part of the mission profile is usually the cruise flight, it is not the critical design point for AoA Angle of attack of a VVG a VTP.
    [Show full text]
  • CFD Analysis of Wing Trailing Edge Vortex Generator Using Serrations
    EPJ Web of Conferences 67, 0 20 02 (2014) DOI: 10.1051/epjconf/20146702002 C Owned by the authors, published by EDP Sciences, 2014 CFD analysis of wing trailing edge vortex generator using serrations H. A. Alawadhi1,a, A. G. Alex1, and Y. H. Kim2 1Emirates Aviation College, Aeronautical Engineering Department, 53044, Dubai, UAE 2Emirates Aviation College, Faculty of Aerodynamics, Aeronautical Engineering Department, 53044, Dubai, UAE Abstract. This study presents computational results of a NACA0012 base wing with the trailing edge modified to incorporate triangular serrations. The effect of the serrations were investigated in three stages, the deflection angle of the serration with respect to the wing chord were examined from -90° to 90° at 10° intervals; the results obtained showed that although larger deflection induces a stronger vorticity magnitude, the strength of the vortex decays faster than compared to smaller deflections. Moreover, the vorticity profile downstream of the wing varies with deflection angle of the serration. Next, the addition of a Clark Y flap to the base wing to analyze the flow pattern and the effect on the flow separation; without serrations attached to the base wing trailing edge, at a high angle of attack, the flow will separate early and would render the flap less effective. The Vortex generator energizes the boundary layer and encourages the flow to remain attached to the flap, allowing for a greater range flap deflection. A wind tunnel experiment was developed and conducted to substantiate the computational analysis in a real world scenario. There was a positive correlation between the results obtained experimentally and computationally.
    [Show full text]
  • File:Thinking Obliquely.Pdf
    NASA AERONAUTICS BOOK SERIES A I 3 A 1 A 0 2 H D IS R T A O W RY T A Bruce I. Larrimer MANUSCRIP . Bruce I. Larrimer Library of Congress Cataloging-in-Publication Data Larrimer, Bruce I. Thinking obliquely : Robert T. Jones, the Oblique Wing, NASA's AD-1 Demonstrator, and its legacy / Bruce I. Larrimer. pages cm Includes bibliographical references. 1. Oblique wing airplanes--Research--United States--History--20th century. 2. Research aircraft--United States--History--20th century. 3. United States. National Aeronautics and Space Administration-- History--20th century. 4. Jones, Robert T. (Robert Thomas), 1910- 1999. I. Title. TL673.O23L37 2013 629.134'32--dc23 2013004084 Copyright © 2013 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks. Introduction v Chapter 1: American Genius: R.T. Jones’s Path to the Oblique Wing .......... ....1 Chapter 2: Evolving the Oblique Wing ............................................................ 41 Chapter 3: Design and Fabrication of the AD-1 Research Aircraft ................75 Chapter 4: Flight Testing and Evaluation of the AD-1 ................................... 101 Chapter 5: Beyond the AD-1: The F-8 Oblique Wing Research Aircraft ....... 143 Chapter 6: Subsequent Oblique-Wing Plans and Proposals ....................... 183 Appendices Appendix 1: Physical Characteristics of the Ames-Dryden AD-1 OWRA 215 Appendix 2: Detailed Description of the Ames-Dryden AD-1 OWRA 217 Appendix 3: Flight Log Summary for the Ames-Dryden AD-1 OWRA 221 Acknowledgments 230 Selected Bibliography 231 About the Author 247 Index 249 iii This time-lapse photograph shows three of the various sweep positions that the AD-1's unique oblique wing could assume.
    [Show full text]
  • Qtr 03 09 a Quarterly Publication Boeing.Com/Commercial/ Aeromagazine
    QTR_03 09 A QUARTERLY PUBLICATION BOEING.COM/COMMERCIAL/ AEROMAGAZINE Special Issue on Operational Efficiency and Environmental Performance: 777 Performance Improvement Blended Winglets Efficient Crew Management Carbon Brakes Fuel Conservation Real-Time Airplane Monitoring Effective Flight Plans AERO Cover photo: Boeing airplane in production. AERO Contents Special Issue: Operational Efficiency and Environmental Performance 03 Boeing technologies are helping operators be more efficient. Our goal is to Operational Efficiency help you drive reductions in fuel burn while increasing the efficiency of individual and Environmental airplanes and entire fleets. Performance Opportunities to improve operational efficiency can be found in all phases of an airplane’s life cycle. 05 Delivering Fuel and Emissions Savings for the 777 09 Blended Winglets Improve 05 Performance 13 Crew Management Tools Improve Operating Efficiency 17 Operational Advantages of Carbon Brakes 17 19 Fuel Conservation Information on 09 MyBoeingFleet Web Portal 22 Monitoring Real-Time Environmental Performance 27 Effective Flight Plans Can Help Airlines Economize 01 WWW.BOEING.COM/COMMERCIAL/AEROMAGAZINE Issue 35_Quarter 03 | 2009 AERO Publisher Design Cover photography Editorial Board Shannon Frew Methodologie Jeff Corwin Gary Bartz, Frank Billand, Richard Breuhaus, Darrell Hokuf, Al John, Doug Lane, Jill Langer, Duke McMillin, Wade Price, Bob Rakestraw, Editorial director Writer Printer Frank Santoni, Jerome Schmelzer, Paul Victor, Constantin Zadorojny Jill Langer Jeff Fraga
    [Show full text]
  • An Application of Vortex Generators to Single Slotted Flap
    N PS ARCHIVE 1966 KIRBY, A. AN APPLICATION OF VORTEX GENERATORS TO A SINGLE SLOTTED FLAP by Lt. A.L G. Kirby Jr. USN Lt. F. M. Graham USN May 1964 PRINCETON UNIVERSITY DEPARTMENT OF CTHcsis K49 AEROSPACE AND MECHANICAL SCIENCES dbibrary TJ. S. Naval Pt»tgracfun>f» <W«nf Monterey. < lal'forni AN APPLICATION OF VORTEX GENERATORS TO A SINGLE SLOTTED FLAP by Lt. AV G. Kirby Jr. USN Lt. F. M. Graham USN May 1964 Submitted in partial fulfillment of the requirements for the Degree Of Master of Science in Engineering from Princeton University yt-l&Ztfj A. Library bch-iti„h««i Naval Postgraduate 0< s . Monterey, California ACKNOWLEDGEMENT The authors wish to express their appreciation to Kr. Thomas 3. Sweeney for his ideas, guidance, and assistance throughout this in- vestigation, and to the Hangar staff for their assistance in in- stalling the required instrumentation and in performing the neces- sary maintenance to keep the aircraft flyable during this investi- gation. The authors acknowledge with gratitude the opportunities for postgraduate education provided by the United States Navy. Appreciation is also expressed to Kr. Marcus Knowlton and Mr. William James for their assistance during the wind tunnel phase of this investigation. To Mrs. Geraldine Fudge we are indebted for her perseverence in typing this manuscript. TABLE OF COKTiftlTS Page Sunun:. -'; . « In tro 'ion List oJ bols Specifics tions . Equipment Aircraft 5 VH. nd Tunnel 5 Model Construction 7 Procedures * 10 Introduction 10 Wind Tunnel 10 Flight Testing 13 Power Required 15 Results 17 Wind Tunnel 17 Flight Test 13 Discussion • 20 Conclusions 25 References 27 Figures 28 AN APPLICATION OF VOR ATORS TO A SINGLE SLOTTED FLAP SUMMARY With the current interest ir V/STOL aircraft, there have beer, various devices designed to improve the take-off and landing character- istics of an aircraft by delaying the flow separation in the preset ce of adverse pressure gradients.
    [Show full text]
  • Coping with Wake Vortex
    ICAS 2002 CONGRESS COPING WITH WAKE VORTEX Klaus-Uwe Hahn Institute of Flight Research, German Aerospace Center (DLR) Lilienthalplatz 7, 38108 Braunschweig, Germany Keywords: wake vortex, encounter, control, safety, separation distance Abstract MTOW maximum take-off weight nm nautical mile The well known phenomenon of wake vortices P2P probabilistic two phase model behind a lift producing wing can adversely af- r radius / radial co-ordinate fect flight safety if encountered by trailing air- ROT runway occupation time craft. The strength of the vortices increases with s spanwise load factor SD separation distance the weight of the vortex generating aircraft. t time co-ordinate Therefore, weight dependent separation dis- T thrust, time constant tances have been established for approach and v lateral velocity component landing to avoid dangerous wake vortex en- V airspeed (no index), velocity counters. These proven separation distances w vertical velocity component Wweight have to be investigated carefully with the aim to α angle of attack discover possible margins to be used to solve β angle of sideslip the current and future capacity problems at air- χ flight path azimuth ports. This demand forms the need for more γ flight path angle flexible separation procedures taking into ac- η elevator deflection count the actual weather situation and the pa- ν effective viscosity ρ air density rameters of the individual aircraft pairing. ξ Separation reductions can be achieved by wake aileron deflection ζ rudder deflection vortex avoidance using prediction systems for ∆ difference the wake vortex development and movement. Φ bank angle The hazardous areas around a wake vortex can Θ pitch angle be approximated by the simple geometry of a ψ azimuth rectangle or an ellipse according to the aircraft indices pairing, the actual weather dependent decay ccore F follower aircraft and the available control power for vortex com- FB feedback pensation.
    [Show full text]
  • Optimization of a Vortex Generator Configuration for a 1/4-Scale Piper Cherokee Wing
    Theses - Daytona Beach Dissertations and Theses Spring 1999 Optimization of a Vortex Generator Configuration for a 1/4-Scale Piper Cherokee Wing Kerri A. Raykowski Embry-Riddle Aeronautical University - Daytona Beach Follow this and additional works at: https://commons.erau.edu/db-theses Part of the Aerospace Engineering Commons Scholarly Commons Citation Raykowski, Kerri A., "Optimization of a Vortex Generator Configuration for a 1/4-Scale Piper Cherokee Wing" (1999). Theses - Daytona Beach. 172. https://commons.erau.edu/db-theses/172 This thesis is brought to you for free and open access by Embry-Riddle Aeronautical University – Daytona Beach at ERAU Scholarly Commons. It has been accepted for inclusion in the Theses - Daytona Beach collection by an authorized administrator of ERAU Scholarly Commons. For more information, please contact [email protected]. OPTIMIZATION OF A VORTEX GENERATOR CONFIGURATION FOR A 1/4-SCALE PIPER CHEROKEE WING by Kerri A. Raykowski A thesis submitted to the Aerospace Engineering Department in partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering Embry-Riddle Aeronautical University Daytona Beach, Florida Spring 1999 UMI Number: EP31919 INFORMATION TO USERS The quality of this reproduction is dependent upon the quality of the copy submitted. Broken or indistinct print, colored or poor quality illustrations and photographs, print bleed-through, substandard margins, and improper alignment can adversely affect reproduction. In the unlikely event that the author did not send a complete manuscript and there are missing pages, these will be noted. Also, if unauthorized copyright material had to be removed, a note will indicate the deletion.
    [Show full text]