2 edition of Study of metallic structural design concepts for an arrow wing supersonic cruise configuration found in the catalog.
Study of metallic structural design concepts for an arrow wing supersonic cruise configuration
M. J Turner
by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield, Va
Written in English
|Statement||M. J. Turner and D. L. Grande, Boeing Commercial Airplane Company ; prepared for Langely Research Center|
|Series||NASA contractor report ; NASA CR-2743, NASA contractor report -- NASA CR-2743|
|Contributions||Grande, D. L., joint author, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Boeing Commercial Airplane Company|
|The Physical Object|
|Pagination||vii, 141 p. :|
|Number of Pages||141|
of wing structural mass and wing main vibration modes, related to the variations on the wing geometry, for a given aircraft mass and design load factor. These intermediate features are the basis for the main goal - to obtain the best compromise between aerodynamics and structures, in terms of wing planform. The. 1. Introduction. Supersonic aircrafts are capable of flying at speeds greater than mi/h ( km/h) but less than mi/h ( km/h), and the Mach number M is greater than one, 1 Cited by:
In design and finite element analysis of aircraft wing using ribs and spars, an aircraft wing is designed and modeled in 3D modeling software Pro/Engineer. The wing is modified by attaching ribs and spars in order to increase the strength of the wing. The materials used for aircraft wings are mostly metallic alloys. In thisFile Size: 1MB. Folded wing concepts such as those used in many World War II vintage aircraft could be used to increa e ground clearance for take-off and landing. However, folded wing mechanisms will undoubtedly add weight back to the vehicle which will negate the benefit of drag reduction. o o Figure 49 -Folded Wing Configuration for Take-Off and Landing.
“Our design reduces the airplane’s noise signature to more of a ‘heartbeat’ instead of the traditional sonic boom that’s associated with current supersonic aircraft in flight today.” NASA awarded the design contract to Lockheed in , and wind tunnel tests of the resulting scale model are expected to conclude mid-year. The X was the first manned aircraft in which aerodynamic heating was the dominant problem of structural design. It was, of course, out of the question in to hope to be able to identify an optimum structural concept representative of distant future developments and no .
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Study of metallic structural design concepts for an arrow wing supersonic cruise configuration. [Washington]: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.
several variants of the arrow wing supersonic cruise vehicle. The resulting structural weights provide a measure of the structural efficiency of the plan- form geometry, structural layout, type of construction, and type of material including composites.
A study was conducted to determine the material distribution for a base- line metallic. Study of Metallic Structural Design Concepts for an Arrow Wing Supersonic Cruise Configuration M. Turner and D. Grande Boeing Commercial Airplane Company Seattle, Washington Prepared for Langley Research Center under Contract NAS National Aeronautics and Space Administration Scientific and Technical.
Full text of "NASA Technical Reports Server (NTRS) Arrow-wing supersonic cruise aircraft structural design concepts 2: Sections 7 through 11" See other formats. Structural Design Introduction Gail Chapline Orbiter Structural Design Thomas Moser The additional load caused higher bending and torsion on the wing structure, exceeding design limits.
The flight limits, in terms of angle of attack and sideslip, the integrated metallic composite construction reduced the thrust structure weight by 21%, or. Full text of "DTIC ADA Supersonic Cruise Research Part 2." See other formats.
W.H. Mason Introduction 1/16/18 Figure Ikelos (Dave Etchells, Loughborough Univ, UK) Figure is also from a senior design project,5 and is a roadable aircraft, sometimes called a flying car.
Some of the details of this concept, and some. This study has for an aim the creation of an preliminary design of the primary structure of an aircraft wing all made of composite (Fig.
1); product of the work developed by the eighth class of the PEE; and comparison to the same design in aluminum. Figure 1: Strider: The project developed by the 8th class of : João Marcelo de Castro, Flavio Luiz de Silva Bussamra. Study of Optimal Design of Spar Beam for the Wing of an Aircraft 1Ajith V S, 2Dr.
Ravikumar Paramasivam, 3K Vidhya 1Asst. Professor, Jawaharlal College of Engineering and Technology, 2Professor, ARJ College of Engineering and Technology, 3Asst. Professor, Jawaharlal College of Engineering and Technology.
In this paper, by means of computational fluid dynamics, a significant study has been made on the effects of geometric parameters of wing with capability of flying efficiently and cost-effectively at supersonic condition. Multi-objective optimization has been performed for the aerodynamic shape optimization of the wing configuration.
The three-dimensional wing shape Cited by: 2. Numerical examples in the paper include the case of an aircraft wing structural box with thousands of degrees of freedom and constraints, and.
A structural design study was made, to assess the relative merits of various metallic structural concepts and materials for an advanced supersonic aircraft cruising at Mach The goal of this work is the multi-point aerodynamic design of a supersonic wing by means of the high efficient and global wing design methodology, which includes Kriging based multi-objective genetic algorithm (MOGA) , and the modified PARametric SECtion (PARSEC) airfoil representation .
This study considers the design problem which has two. The Carlson correction for supersonic linear theory wing calculations is applied at wing control points.
If desired, COREL will produce conical panel pressure data for further processing by W12SC3. W12SC3 can perform the following aerodynamic functions: 1) full analysis, 2) full design, 3) full optimization, 4) mixed design-analysis, and 5.
The purpose of this book is to illustrate step by step the design of the Composite Wing Structure of the external wing for an Unmanned Aerial Vehicle- UAV. The design is conducted using software tools for Finite Element Analysis, such as, NASTRAN and ANSYS to find the structural integrity limits for composite materials and : Pedro Luis Jimenez Soler.
Structural design of a uav wing using finite element method farrukh mazhar 3. Design and Analysis of Wing of an Ultralight Aircraft Yuvaraj S R 1, Subramanyam P 2 4. Optimization of aircraft wing with composite material shabeer kp1, murtaza m a2 5.
Design and Finite Element Analysis of Aircraft Wing 6. Supersonic Wing Design The wing of a second generation supersonic transport will most likely have its leading edge(s) swept behind the Mach cone. Higher speeds mean higher sweep angles and less efﬁcient subsonic aerodynamics unless the aircraft has variable geometry.
At cruise conditions the ﬂow approaching the wing is that behind the shock. Supersonic Wing Design Over a period of years, NASA-Langley has developed a basic computerized series of supersonic design and analysis methods for aerodynamic configuration studies. The methods are characterized by their reliability in use and input simplicity.
Low-Speed Arorodynamic Characteristics of a Modified Arrow-Wing Supersonic Transport Configuration with High-Lift Devices (NASA TM X ) [Donald Loving, James Blackwell] on *FREE* shipping on qualifying offers.
68 pages. Title: Design Optimization of a Composite Wing Box for High-Altitude Long-Endurance Aircraft Institution: Embry-Riddle Aeronautical University Degree: Master of Science in Mechanical Engineering Year: A design optimization process is developed to define the wing box structure for High-Altitude Long-Endurance Aircraft (HALE).
Supersonic Aerodynamic Design from the Virginia Tech Aircraft Design Information Sources pages. C.F. Brown and F.E. McLean, "The Problem of Obtaining High Lift-Drag Ratios at Supersonic Speeds," Journal of the Aeronautical Sciences, Vol.
26, pp.This is one of the first papers to discuss crossflow shock waves.structural design result, structural analysis was performed by using FEM code.
From the structural analysis on the first design configuration, some modifications were drawn due to weak area on buckling and a bit heavier than the target weight. The final structural configuration was fixed through several repeated design modifications and analyses.A clean flying wing is sometimes presented as theoretically the most aerodynamically efficient (lowest drag) design configuration for a fixed wing aircraft.
It also would offer high structural efficiency for a given wing depth, leading to light weight and high fuel efficiency. Because it lacks conventional stabilizing surfaces and the associated control surfaces, in its purest form the .