2018-19 Design, Build, Fly Q&A #1
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Aiaa 96-2517-Cp Twin Tail/Delta Wing Configuration Buffet
AIAA 96-2517-CP TWIN TAIL/DELTA WING CONFIGURATION BUFFET DUE TO UNSTEADY VORTEX BREAKDOWN FLOW Osama A. Kandil, Essam F. Sheta and Steven J. Massey Aerospace Engineering Department Old Dominion University Norfolk, VA 23529 The 14th AIAA Applied Aerodynamics Conference New Orleans, LA-June 18-20, 1996 I | For Permission to copy or republish, contact the American Institute of Aeronautics and Astronautics 370 12Enfant Promenade, S. W., Washington, D.C. 20024 / NASA-CR-203259 o J _"_G"7"_ COMPUTATION AND VALIDATION OF FLUID/ STRUCTURE TWIN TAIL BUFFET RESPONSE Osama A. Kandil and Essam F. Sheta Aerospace Engineering Department Old Dominion University, Norfolk, VA 23529, USA C. H. Liu Aerodynamics Methods and Acoustics Branch NASA Langley Research Center, Hampton, VA 23665, USA EUROMECH COLLOQUIUM 349 STRUCTURE FLUID INTERACTION IN AERONAUTICS Institute Fiir Aeroelastik, GSttingen, Germany September 16-18, 1996 COMPUTATION AND VALIDATION OF FLUID/STRUCTURE TWIN TAIL BUFFET RESPONSE Osama A. Kandil 1 and Essam F. Sheta: Aerospace Engineering Department Old Dominion University, Norfolk, VA 23529, USA and C. H. Liu 3 Aerodynamics Methods and Acoustics Branch NASA Langley Research Center, Hampton, VA 23665, USA ABSTRACT The buffet response of the flexible twin-tail/delta wing configuration-a multidisciplinary problem is solved using three sets of equations on a multi-block grid structure. The first set is the unsteady, compressible, full Navier-Stokes equations which are used for obtaining the flow-filed vector and the aerodynamic loads on the twin tails. The second set is the coupled aeroelastic equations which are used for obtaining the bending and torsional deflections of the twin tails. -
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 -
General Aviation Aircraft Design
Contents 1. The Aircraft Design Process 3.2 Constraint Analysis 57 3.2.1 General Methodology 58 1.1 Introduction 2 3.2.2 Introduction of Stall Speed Limits into 1.1.1 The Content of this Chapter 5 the Constraint Diagram 65 1.1.2 Important Elements of a New Aircraft 3.3 Introduction to Trade Studies 66 Design 5 3.3.1 Step-by-step: Stall Speed e Cruise Speed 1.2 General Process of Aircraft Design 11 Carpet Plot 67 1.2.1 Common Description of the Design Process 11 3.3.2 Design of Experiments 69 1.2.2 Important Regulatory Concepts 13 3.3.3 Cost Functions 72 1.3 Aircraft Design Algorithm 15 Exercises 74 1.3.1 Conceptual Design Algorithm for a GA Variables 75 Aircraft 16 1.3.2 Implementation of the Conceptual 4. Aircraft Conceptual Layout Design Algorithm 16 1.4 Elements of Project Engineering 19 4.1 Introduction 77 1.4.1 Gantt Diagrams 19 4.1.1 The Content of this Chapter 78 1.4.2 Fishbone Diagram for Preliminary 4.1.2 Requirements, Mission, and Applicable Regulations 78 Airplane Design 19 4.1.3 Past and Present Directions in Aircraft Design 79 1.4.3 Managing Compliance with Project 4.1.4 Aircraft Component Recognition 79 Requirements 21 4.2 The Fundamentals of the Configuration Layout 82 1.4.4 Project Plan and Task Management 21 4.2.1 Vertical Wing Location 82 1.4.5 Quality Function Deployment and a House 4.2.2 Wing Configuration 86 of Quality 21 4.2.3 Wing Dihedral 86 1.5 Presenting the Design Project 27 4.2.4 Wing Structural Configuration 87 Variables 32 4.2.5 Cabin Configurations 88 References 32 4.2.6 Propeller Configuration 89 4.2.7 Engine Placement 89 2. -
Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment
University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 5-2006 Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment Scott Bennett Trail University of Tennessee - Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Aerospace Engineering Commons Recommended Citation Trail, Scott Bennett, "Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment. " Master's Thesis, University of Tennessee, 2006. https://trace.tennessee.edu/utk_gradthes/1816 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 Scott Bennett Trail entitled "Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment." 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 Aviation Systems. Robert B. Richards, Major Professor We have read this thesis and recommend its acceptance: Rodney Allison, Frank Collins 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 Scott Bennett Trail entitled “Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment”. -
Design, Analysis and Optimization of Folding Wing Mechanism for Effective Utilization of Air Side Area
ISSN (O): 2393-8609 International Journal of Aerospace and Mechanical Engineering Volume 3 – No.5, September 2016 DESIGN, ANALYSIS AND OPTIMIZATION OF FOLDING WING MECHANISM FOR EFFECTIVE UTILIZATION OF AIR SIDE AREA Dishant Kothia Japneet Singh Akanksha Dadhich University of Petroleum and University of Petroleum and University of Petroleum and Energy Studies, Dehradun Energy Studies, Dehradun Energy Studies, Dehradun [email protected] [email protected] akankshadadhich4@gmai om l.com ABSTRACT ground operations altogether, a folding wing design has been This paper aims to suggest a solution for the problem of employed to Boeing 787. disproportionately lesser growth of airside space with respect to growth of passengers/air traffic by using wing folding 2. LITERARY REVIEW mechanism in aircrafts while on ground. A study of air traffic A study was done for past World War-2 era mechanisms, growth was followed by selecting STO-wing mechanism currently used mechanisms in small private aircrafts and also which met with desired requirements. spring loaded mechanisms used in some modern cruise missiles. The naval helicopters and the ship-borne aircraft- Boeing 787-8 Dreamliner was selected as base aircraft as it carriers have been the pioneer, in the sphere of foldable main- met certain criterion and analysis for mechanism was started. planes and tail-planes. Many patents have been created by the Different mechanisms of implementing STO-wing are leading designers and manufacturers. The merits and demand discussed, and calculation for rod-lug mechanism which was of a folding wing mechanism to potentially cease the ill- finally chosen is shown. Its FEM analysis was carried out in effects of traffic growth in aviation industry have paved the ANSYS 14.5 along with mesh sensitivity study. -
Conceptual Design of Self-Expanding/Folding Extremely Large Aspect Ratio Wing Airplane
DOI: 10.13009/EUCASS2017-209 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Conceptual Design of Self-Expanding/Folding Extremely Large Aspect Ratio Wing Airplane Zhou Xiaopeng* and Chen Haixin* * School of Aerospace Engineering, Tsinghua University Beijing, China Abstract This paper puts forward the idea of self-expanding/folding wing and makes a preliminary conceptual design of extremely large aspect ratio airplane based on this idea. The expanding and folding process in flight is carried out by the movement of the rudder surfaces, the adjustment of distributed propulsion system and the active flight control technology. The preliminary conceptual design and performance analysis indicates that the extremely large aspect ratio airplane based on self-expanding/folding wing can obviously improve the airplane’s airport runway adaptability, take-off and landing performance, keeping a high cruise lift-drag ratio, with acceptable increasing of take-off weight. 1. Introduction 1.1 Requirement for extremely large aspect ratio wing Reducing drag has always been one of the first considerations in aircraft design process. The extremely large aspect ratio wing has great advantages in cutting down induced drag, which leading to widely applications in glider, long- endurance UAV, high-altitude launch aircraft and other aircrafts. Finding out a suitable configuration to carry out the extremely large aspect ratio wing, keeping the advantages and overcoming the shortcomings, is the focus of high- altitude long-endurance aircraft and other similar aircrafts design. 1.2 Implement methods of extremely large aspect ratio wing airplane The increasing wingspan of conventional cantilever wings is limited by the conditions for take-off and landing of airport runways, poor flight conditions of lower atmosphere owing to unstable airflow, structural strength and rigidity of aircraft, and flight handling qualities. -
Review Paper on Wing Folding Mechanism
ISSN (O): 2393-8609 International Journal of Aerospace and Mechanical Engineering Volume 6 – No.2, September 2019 Review Paper on Wing Folding Mechanism Aman Upadhyay Harsh Mehra BE Mechanical Engineering BE Mechanical Engineering Chandigarh University Chandigarh University [email protected] [email protected] ABSTRACT This review paper discusses the solution to the problem In this paper, we will describe the importance and arising due to this increased traffic and the availability of less implementation of the wing folding mechanism. These days space at the airport to park the aircraft. Wing folding we are seeing the growth of air passengers, air traffic and the mechanism can be implemented to passenger aircraft to solve problem lesser space at the airport for parking of aircraft. This this problem. Once, an efficient wing folding mechanism is paper reviews the wing folding mechanism and its developed it can be implemented to the huge airliners like implementation to save the airport space to accommodate Airbus A380 and Boeing 777X or many other passenger more aircrafts. Wing folding mechanism is used to fold the aircraft. This will result in saving a lot of space at airport wings of aircraft parked at airport to save the space and reduce results in lesser demands of extra terminals. It will also result the wingspan. Further, this wing folding mechanism is also in time-saving as the wing can be folded while taxing on implemented in flying cars. runways more aircraft can move on adjacent runways and transportation of the aircraft will be easier. Keywords This paper discusses different wind folding mechanism Wing Folding Mechanism, Flying Cars, Folding Wing, available and their implementation. -
Wing, Fuselage and Tail • Mainplane: Airfoil Cross-Section Shape, Taper Ratio Selection, Sweep Angle Selection, Wing Drag Estimation
Design Of Structural Components - Wing, Fuselage and Tail • Mainplane: Airfoil cross-section shape, taper ratio selection, sweep angle selection, wing drag estimation. Spread sheet for wing design. • Fuselage: Volume consideration, quantitative shapes, air inlets, wing attachments; Aerodynamic considerations and drag estimation. Spread sheets. • Tail arrangements: Horizontal and vertical tail sizing. Tail planform shapes. Airfoil selection type. Tail placement. Spread sheets for tail design Main Wing Design 1. Introduction: Airfoil Geometry: • Wing is the main lifting surface of the aircraft. • Wing design is the next logical step in the conceptual design of the aircraft, after selecting the weight and the wing-loading that match the mission requirements. • The design of the wing consists of selecting: i) the airfoil cross-section, ii) the average (mean) chord length, iii) the maximum thickness-to-chord ratio, iv) the aspect ratio, v) the taper ratio, and Wing Geometry: vi) the sweep angle which is defined for the leading edge (LE) as well as the trailing edge (TE) • Another part of the wing design involves enhanced lift devices such as leading and trailing edge flaps. • Experimental data is used for the selection of the airfoil cross-section shape. • The ultimate “goals” for the wing design are based on the mission requirements. • In some cases, these goals are in conflict and will require some compromise. Main Wing Design (contd) 2. Airfoil Cross-Section Shape: • Effect of ( t c ) max on C • The shape of the wing cross-section determines lmax for a variety of the pressure distribution on the upper and lower 2-D airfoil sections is surfaces of the wing. -
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. -
Advanced Pilot Training (APT T-X) Aircraft and 46 Ground-Based Training Systems (GBTS) to Replace the Existing Fleet of T-38C Jet Trainers
Air Force T-7A Red Hawk Trainer Updated September 18, 2019 Congressional Research Service https://crsreports.congress.gov R44856 Air Force T-7A Red Hawk Trainer Summary NOTE: This report was originally written by Ceir Coral while he was an Air Force Fellow at the Congressional Research Service. Since his departure, it has been maintained by Jeremiah Gertler of CRS. On September 27, 2018, the United States Air Force (USAF) awarded The Boeing Company a contract, worth up to $9.2 billion, to procure 351 Advanced Pilot Training (APT T-X) aircraft and 46 Ground-Based Training Systems (GBTS) to replace the existing fleet of T-38C jet trainers. The Air Force had originally valued the contract at roughly $19.7 billion. Information on the value of other competitors’ bids was not available. On September 16, 2019, Acting Secretary of the Air Force Matthew Donovan announced that in service, the T-X aircraft would be known as the T-7A Red Hawk. In this report, “APT T-X” will be used to identify the entire training system, while “T-7A” will refer to the aircraft portion of that system. The FY2020 Administration budget request included $348.473 million for the APT T-X. According to the USAF, the current T-38C trainer fleet is old, costly, and outdated, and lacks the technology to train future pilots for fifth-generation fighter and bomber operations. Based on Air Education Training Command’s evaluation of the required capabilities to train future pilots for fifth-generation fighters and bombers, the T-38C falls short in 12 of 18 capabilities, forcing the USAF to train for those capabilities in operational units where flying hours are costly and can affect fleet readiness.