A Look Back at Flying Wings Part 1
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CESSNA WING TIPS - EMPENNAGE TIPS CESSNA WING TIPS These Wing Tip Kits Consist of a Left and Right Hand Drooped Fiberglass Wing Tip
CESSNA WING TIPS - EMPENNAGE TIPS CESSNA WING TIPS These wing tip kits consist of a left and right hand drooped fiberglass wing tip. These wing tips are better than those manufactured by Cessna because they are made of fiberglass rather than a royalite type material, that bends and CM cracks after a short time on the aircraft. The superior epoxy rather than polyester fiberglass is used. Epoxy fiberglass has major advantages over a royalite type material; It is approximately six timesstronger and twelve times stiffer, it resists ultraviolet light and weathers better, and it keeps its chemical composition intact much longer. With all these advantages, they will probably be the last wingtips that will ever have to be installed on the aircraft. Should these wing tips be damaged through some unforeseen circumstances, they are easily repairable due to their fiberglass construc- tion. These kits are FAA STC’d and manufactured under a FAA PMA authority. The STC allows you to install these WP modern drooped wing tips, even if your aircraft was not originally manufactured with this newer, more aerodynamically efficient wingtip. *Does not include the Plate lens. Plate lens must be purchased separately. **Kits includes the left hand wing tip, right hand wing tip, hardware, and the plate lens Cessna Models Kit No.** Price Per Kit All 150, A150, 152, A152, 170A & B, P172, 175, 205 &L19, 172, 180, 185 for model year up through 1972.182, 206 for 05-01526 . model year up through 1971, 207 from 1970 and up (219-100) ME 05-01545 172, R172K(172XP), 172RG, 180, 185 for model year 1973 and up, 182, 206 for model year 1972 and up. -
Aircraft Winglet Design
DEGREE PROJECT IN VEHICLE ENGINEERING, SECOND CYCLE, 15 CREDITS STOCKHOLM, SWEDEN 2020 Aircraft Winglet Design Increasing the aerodynamic efficiency of a wing HANLIN GONGZHANG ERIC AXTELIUS KTH ROYAL INSTITUTE OF TECHNOLOGY SCHOOL OF ENGINEERING SCIENCES 1 Abstract Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by evaluating its lift-to-drag ratios with the obtained lift and drag forces. The result from this study showed that the overall efficiency of the wing varied depending on the winglet design, with some designs noticeable more efficient than others according to the CFD-simulations. The shark fin-alike winglet was overall the most efficient design, followed shortly by the famous blended design found in many mid-sized airliners. The worst performing designs were surprisingly the fenced and spiroid designs, which had efficiencies on par with the wing without winglet. 2 Content Abstract 2 Introduction 4 Background 4 1.2 Purpose and structure of the thesis 4 1.3 Literature review 4 Method 9 2.1 Modelling -
Daniel Egger Papers
http://oac.cdlib.org/findaid/ark:/13030/c87w6jb1 Online items available Daniel Egger papers Finding aid prepared and updated by Gina C Giang. Manuscripts Department The Huntington Library 1151 Oxford Road San Marino, California 91108 Phone: (626) 405-2191 Fax: (626) 449-5720 Email: [email protected] URL: http://www.huntington.org © Finding aid last updated June 2019. The Huntington Library. All rights reserved. Daniel Egger papers mssEgger 1 Descriptive Summary Title: Daniel Egger papers Inclusive Dates: 1927-2019 Collection Number: mssEgger Collector: Egger, Daniel Frederic Extent: 3 boxes, 1 oversize folder, 1 flash drive, and 1 tube (1.04 linear feet) Repository: The Huntington Library, Art Collections, and Botanical Gardens Manuscripts Department 1151 Oxford Road San Marino, California 91108 Phone: (626) 405-2191 Fax: (626) 449-5720 Email: [email protected] URL: http://www.huntington.org Abstract: The Daniel Egger papers include correspondence, printed matter, and photographs related to Daniel Egger’s career in the aerospace industry. Language of Material: The records are in English and Spanish. Access Collection is open to qualified researchers by prior application through the Reader Services Department. For more information, please go to following web site . NOT AVAILABLE: The collection contains one flash drive, which is unavailable until reformatted. Please contact Reader Services for more information. RESTRICTED: Tube 1 (previously housed in Box 1, folder 1). Due to size of original, original will be available only with curatorial permission. Publication Rights The Huntington Library does not require that researchers request permission to quote from or publish images of this material, nor does it charge fees for such activities. -
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Nick: Invisibility sounds like something out of a work of Sci-Fi. However, Northrop Grumman’s B2 Spirit is just that. While the B2 is not invisible to the naked eye, it can avoid detection by radar thanks to a specially designed frame and coating that deflects and nullifies radar waves. Radar waves are sent outwards, and bounce off of features such as engines and straight wings. By altering its shape and applying radar absorbent material, the B2 is able to minimize the radar waves that can be analyzed, making the B2 almost impossible to find. On top of being a stealth plane, the B2 is a flying wing, meaning it has no fuselage or tail. The B2 is meant to be a low observable stealth plane used to penetrate anti-aircraft defenses. It can carry both conventional and thermonuclear weapons, and is a unique aircraft that can carry heavy air-to-surface weapons while also remaining in stealth. But where did this technology come from? Daryl: As soon as radar was developed during World War Two, there was a need to evade radar. Efforts were made during and after the war to counter radar, and two German brothers were the first to find a solution. Walter and Reimar Horton were pilots with the German Luftwaffe, but also designed aircraft of their own. One of these was the Horton HO-229 jet, the earliest flying wing propelled by a jet, which also had radar wave absorbing material on the wings. They used a wood-carbon powder to absorb radar waves, making this the earliest stealth plane. -
“Keep the Dream Alive”
February 28, 2015 The 60th Annual Honors and Awards Banquet “Keep the Dream Alive” February 28, 2015 th 60 Honors & Awards Banquet Diamond Anniversary 1 The 60th Annual Honors and Awards Banquet February 28, 2015 National Engineers Week Committees ~ BANQUET COMMITTEE ~ Kenneth Davis, Sonja Domazet, Stephen Guine, William Johnson, Sharlene Katz, Paul Landry, Robert Tarn, Thomas R. Tarn, Charles Volk ~ HONORS & AWARDS COMMITTEE ~ Marek Barylak, Kenneth Davis, Stephen Guine, Sharlene Katz, Paul Landry, Charles Olsefsky, R. Freeman Straub, Robert B. Tarn ~ AWARDS ASSEMBLY ~ Ken Davis, Sonja Domazet, James Flynn, Bill Johnson, Sharlene Katz, Charles Olsefsky ~ HOST / HOSTESSES ~ Olivia Landry, Maria Tarn ~ SOUVENIR PROGRAM GRAPHICS & DESIGN ~ Paul Landry ~ AWARD GRAPHICS ~ Mike Matte ~ AUDIO / VIDEO ~ Swank Audio Visuals, Carlos Guerra ~ BANQUET SETUP / AWARDS DISTRIBUTION ~ Marissa Bayless, Margo Guerra ~ MATH COUNTS ~ Jerry Kraim, Eli Stiny Engineers’ Council Past Presidents 1970 William B. Johnson 1992 Robert Budica 2005 Robert B. Tarn 1980 Clifford B. Shiepe, PE 1993 Lloyd W. Higginbotham, FIAE 2006 Paul F. Landry 1981 Clifford B. Shiepe, PE 1994 Lloyd W. Higginbotham, FIAE 2007 Paul F. Landry 1982 Lloyd W. Higginbotham, FIAE 1995 Lloyd W. Higginbotham, FIAE 2008 Patrick Berbon 1983 William F. Hassel, PE, FIAE 1996 Lloyd W. Higginbotham, FIAE 2009 Dr. Charles H. Volk 1984 Clifford Terry 1997 Lloyd W. Higginbotham, FIAE 2010 Dr. Charles H. Volk 1985 Roland V. Roggero 1998 Lloyd W. Higginbotham, FIAE 2011 Kenneth G. Davis 1986 James P. Ritchey 1999 Lloyd W. Higginbotham, FIAE 2012 Kenneth G. Davis 1987 James P. Ritchey 2000 Lloyd W. Higginbotham, FIAE 2013 Sonja Domazet 1988 Harlan L. Russ 2001 Lloyd W. -
Wing Tip.Qxd
WINGTIP COUPLING AT 15,000 FEET Dangerous Experiments by C.E. “Bud” Anderson ingtip coupling evolved from an invention by Dr. Richard Vogt, a German scientist who emigrated to W the U.S. after WW II. The basic con- cept involved increasing an aircraft’s range by attaching two “free-floating,” fuel-carrying aerodynamic panels to the wingtips. This could be accomplished without undue struc- tural weight penalties as long as the panels were free to articulate and support themselves with their own aerodynamic lift. The panels would increase the basic wing configuration’s aspect ratio and would therefore significantly reduce induced drag; the “free” extra fuel car- ried by this more efficient wing would consid- erably increase an aircraft’s range. Soon, other logical uses of this unusual concept became apparent: for example, two escort fighters might be carried along “free” on a large bomber without sacrificing its range. To be feasible, the wingtip extensions, But there was also the problem of how such fuel-carrying extensions could be handled on the ground. How would they be supported without airflow to or panels, whatever they were, would have to hold them up?—perhaps by the use of a retractable outrigger landing gear, but what about runway width requirements? And—the big question—what about be kept properly aligned, preferably by a sim- the stability and control problems that might be induced by such a configura- ple and automatic flight-control system. tion; would the extensions be easy to control? Many questions are also immedi- 64 FLIGHT JOURNAL The second wingtip-coupling experiment involved an ETB-29A and two EF-84Bs (photo courtesy of Peter M. -
Fast 49 Airbus Technical Magazine Worthiness Fast 49 January 2012 4049July 2007
JANUARY 2012 FLIGHT AIRWORTHINESS SUPPORT 49 TECHNOLOGY FAST AIRBUS TECHNICAL MAGAZINE FAST 49 FAST JANUARY 2012 4049JULY 2007 FLIGHT AIRWORTHINESS SUPPORT TECHNOLOGY Customer Services Events Spare part commonality Ensuring A320neo series commonality 2 with the existing A320 Family AIRBUS TECHNICAL MAGAZINE Andrew James MASON Publisher: Bruno PIQUET Graham JACKSON Editor: Lucas BLUMENFELD Page layout: Quat’coul Biomimicry Cover: Radio Altimeters When aircraft designers learn from nature 8 Picture from Hervé GOUSSE ExM Company Denis DARRACQ Authorization for reprint of FAST Magazine articles should be requested from the editor at the FAST Magazine e-mail address given below Radio Altimeter systems Customer Services Communications 15 Tel: +33 (0)5 61 93 43 88 Correct maintenance practices Fax: +33 (0)5 61 93 47 73 Sandra PREVOT e-mail: [email protected] Printer: Amadio Ian GOODWIN FAST Magazine may be read on Internet http://www.airbus.com/support/publications ELISE Consulting Services under ‘Quick references’ ILS advanced simulation technology 23 ISSN 1293-5476 Laurent EVAIN © AIRBUS S.A.S. 2012. AN EADS COMPANY Jean-Paul GENOTTIN All rights reserved. Proprietary document Bruno GUTIERRES By taking delivery of this Magazine (hereafter “Magazine”), you accept on behalf of your company to comply with the following. No other property rights are granted by the delivery of this Magazine than the right to read it, for the sole purpose of information. The ‘Clean Sky’ initiative This Magazine, its content, illustrations and photos shall not be modified nor Setting the tone 30 reproduced without prior written consent of Airbus S.A.S. This Magazine and the materials it contains shall not, in whole or in part, be sold, rented, or licensed to any Axel KREIN third party subject to payment or not. -
Commercial Aircraft Performance Improvement Using Winglets
Nikola N. Gavrilović Commercial Aircraft Performance Graduate Research Assistant Improvement Using Winglets University of Belgrade Faculty of Mechanical Engineering Aerodynamic drag force breakdown of a typical transport aircraft shows Boško P. Rašuo that lift-induced drag can amount to as much as 40% of total drag at Full Professor cruise conditions and 80-90% of the total drag in take-off configuration. University of Belgrade Faculty of Mechanical Engineering One way of reducing lift-induced drag is by using wing-tip devices. By applying several types of winglets, which are already used on commercial George S. Dulikravich airplanes, we study their influence on aircraft performance. Numerical Full Professor investigation of five configurations of winglets is described and Florida International University preliminary indications of their aerodynamic performance are provided. Department of Mechanical and Materials Engineering, Miami, Florida, USA Moreover, using advanced multi-objective design optimization software an optimal one-parameter winglet configuration was detrmined that Vladimir Parezanović simultaneously minimizes drag and maximizes lift. Researcher Institute PPRIME, CNRS UPR3346 Poitiers, France Keywords: Winglet, Bionics, Computational fluid dynamics, Drag reduction, Lift-induced drag, Optimization 1. INTRODUCTION of soaring birds and their use of tip feathers to control flight, continued on the quest to reduce induced drag The main motivation for using wingtip devices is and improve aircraft performance and further develop reduction of lift-induced drag force. Environmental the concept of winglets in the late 1970s [4]. This issues and rising operational costs have forced industry research provided a fundamental knowledge and design to improve efficiency of commercial air transport and approach required for extremely attractive option to this has led to some innovative developments for improve aerodynamic efficiency of civilian aircraft, reducing lift-induced drag. -
Chapter 12 Design of Control Surfaces
Aileron Design Chapter 12 Design of Control Surfaces From: Aircraft Design: A Systems Engineering Approach Mohammad Sadraey 792 pages September 2012, Hardcover Wiley Publications 12.4.1. Introduction The primary function of an aileron is the lateral (i.e. roll) control of an aircraft; however, it also affects the directional control. Due to this reason, the aileron and the rudder are usually designed concurrently. Lateral control is governed primarily through a roll rate (P). Aileron is structurally part of the wing, and has two pieces; each located on the trailing edge of the outer portion of the wing left and right sections. Both ailerons are often used symmetrically, hence their geometries are identical. Aileron effectiveness is a measure of how good the deflected aileron is producing the desired rolling moment. The generated rolling moment is a function of aileron size, aileron deflection, and its distance from the aircraft fuselage centerline. Unlike rudder and elevator which are displacement control, the aileron is a rate control. Any change in the aileron geometry or deflection will change the roll rate; which subsequently varies constantly the roll angle. The deflection of any control surface including the aileron involves a hinge moment. The hinge moments are the aerodynamic moments that must be overcome to deflect the control surfaces. The hinge moment governs the magnitude of augmented pilot force required to move the corresponding actuator to deflect the control surface. To minimize the size and thus the cost of the actuation system, the ailerons should be designed so that the control forces are as low as possible. -
Theoretical Aspects and Practical Us Age of Hoerner Wing Tip
THEORETICAL ASPECTS AND PRACTICAL US AGE OF HOERNER WING TIP AN EFFICIENT WING TIP-WHAT'S NEEDED? Dr. Hoerner showed that the efficiency of a wing tip depends on six critical areas. His findings were: 1. The tip must be as thin as possible but still maintain a round leading edge. 2. A blending of wing top and bottom surfaces along a straight line. 3. The edge formed at this blend to be as thin as possible. 4. Obtain a sharp trailing edge leading to a corner, this corner to be in a straight a line as possible with the entire wing trailing edge. 5. The top of the tip to remain in a level plane with the top of the wing. 6. The bottom plane to be brought up in a convex curve. The primary reasons for this design are as follows: A square wing tip gives the greatest wing area for the least span. A smoothly finished, thin, leading edge provides for the best possible airflow over the tip. The convex underside accelerates the speed of the air passing under the tip to a velocity more equal to that of the air flowing over the top of the tip, thereby creating streamline flow. This flow reduces turbulence, which markedly decreases the size and intensity of tip vortices. By having a deep, straight trailing edge we are moving the point at which the vortex begins away from and behind the main surface of the wing, which means less drag and better control. By keeping the outermost point of the wing in a level plane with the wing top surface, we effectively increase wing dihedral angles. -
Sherman Oaks, California
Sherman Oaks, California Theodore von Kármán Engineer of the Year Educator of the Year Achievement Award Mr. Eric D. Knutson Dr. Melvin A. Breuer Dr. Buzz Aldrin Director of Advanced Projects Professor Astronaut, Apollo XI Lockheed Martin Skunkworks University of Southern Retired Colonel, USAF Palmdale, California California Author and Space Los Angeles, California Advocate th 56 Annual HONORS AND AWARDS BANQUET Saturday, February 26, 2011 In Celebration of National Engineers Week, February 20-26, 2011 National Engineers Week Committees Banquet Committee: Marek Barylak, Robert Budica, Larry Dalton, Kenneth Davis, Sonja Domazet, Carlos & Margo Guerra, Stephen Guine, William Johnson, Jerry Kraim, Diane Kulisek, Paul Landry, Charles Olsefsky, S. K. Ramesh, Rick Ratcliffe, Ramin Roosta, Noelle Segura, R. Freeman Straub, Robert Tarn, Charles Volk Honors & Awards Committee: Kenneth Davis, Diane Kulisek, Paul Landry, Charles Olsefsky, R. Freeman Straub, Robert Tarn Visual Media Services: Warren Huskey, Mike Matte Awards Assembly Marek Barylak, Larry Dalton, Kenneth Davis, Sonja Domazet, William Johnson, Diane Kulisek, Sharlene Katz, Charles Olsefsky, Ramin Roosta, R. Freeman Straub, Charles Volk Hostesses: Mary Claire Jensen, Mickey Knobloch, Olivia Landry, Maria Tarn Audio/Video: Swank Audio Visuals Award Presenters: Sonja Domazet, Stephen Guine, William Johnson, Paul Landry, Robert Tarn, Charles Volk Banquet Setup/Awards Distribution: Margo Guerra, CSUN Engineering Students Math Counts: Jerry Kraim LA County Science Bowl: Larry Dalton First Robotics: R. Freeman Straub The Engineers’ Council Board of Directors President Vice President Treasurer Secretary Kenneth G. Davis Sonja Domazet Dr. Charles H. Volk Robert B. Tarn Trustees: Dr. Robert J. Budica, Paul F. Landry, Dr. A. F. Ratcliffe, Robert B. -
Development of a Flight Dynamics Model of a Flying Wing Configuration
Master thesis in Aeronautical Engineering Development of a Flight Dynamics Model of a Flying Wing Configuration Candidate Supervisor Jacopo Tonti Prof. Guido De Matteis External supervisor Prof. Arthur Rizzi (Kungliga Tekniska högskolan) Academic Year 2013/2014 cbn 2014 by Jacopo Tonti Some rights reserved. This thesis is available under a Creative Commons CC BY-NC-3.0 IT License. (creativecommons.org/licenses/by-nc/3.0/it/) Alla mia musa , a Vale «As ailerons, these damn spoilers make great rudders!» Bruce Miller, after flying the Marske Pioneer 1A Abstract The subject of UCAV design is an important topic nowadays and many countries have their own programmes. An international group, under the initiative of the NATO RTO AVT-201 Task group, titled “Extended Assessment of Reliable Stability & Control Pre- diction Methods for NATO Air Vehicles”, is currently performing intensive analysis on a generic UCAV configuration, named SACCON. In this thesis the stability and control characteristics of the SACCON are investigated, with the purpose of carrying out a compre- hensive assessment of the flying qualities of the design. The study included the generation of the complete aerodynamic database of the aircraft, on the basis of the experimental data measured during TN2514 and TN2540 campaigns at DNW-NWB low speed wind tunnel. Moreover, system identification techniques were adopted for the extraction of dynamic derivatives from the time histories of forced oscillation runs. The trim of the aircraft was evaluated across the points of a reasonable test envelope, so as to define a set of plausible operative conditions, representing the reference conditions for subsequent linearization of the dynamic model.