3 edition of Current flight test experience related to structural divergence of forward-swept wings found in the catalog.
Current flight test experience related to structural divergence of forward-swept wings
1988 by National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, For sale by the National Technical Information Service] in Edwards, Calif, [Springfield, Va .
Written in English
|Statement||Lawerence S. Schuster and William A. Lokos.|
|Series||NASA technical memorandum -- 100445.|
|Contributions||Lokos, William A., Dryden Flight Research Facility.|
|The Physical Object|
In current practice wind-tunnel testing is used to acquire the loads data, both because the cumulative cost of acquisition via CFD still exceeds the costs of building and testing properly instrumented models, and because a lack of confidence in the reliability of CFD simulations of extreme flight conditions Air traffic is growing at a steady rate of 3% to 5% per year in most regions of the world, implying a doubling every 15–25 years. This requires major advances in aircraft noise reduction at airports, just not to increase the noise exposure due to the larger number of aircraft movements. In fact it can be expected, as a consequence of increased opposition to noise by near airport residents Cited by: 1. Aeroelastic divergence occurs in some wings when the dynamic pressure is suciently large that a change in lift caused by a wing deformation is greater than the structural elastic restoring forces, and the deformation increases until the structural limits are exceeded and the structure fails This tendency for forward swept wings to experience.
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Current Flight Test Experience Related to Structural Divergence of Forward-Swept Wings Lawrence S. Schuster and William A. Lokos NASA Ames Research Center Dryden Flight Research Facility Edwards, California _STRA_ Flight testing the XA forward-swept-wing aircraft has required development of new flight test techniques to accomplish subcriticalFile Size: KB.
Current Flight Test Experience Related to Structural Divergence of Forwa rd-Swept Wings Author: Lawrence S. Schuster and William A.
Lokos Subject: H Keywords: Envelope expansion, Extrapolation techniques, FLEXSTAB, Forward-swept wi ng, In-flight deflection measurement, NASTRAN, Static aeroelasticity, St ructural divergence Created Date.
Get this from a library. Current flight test experience related to structural divergence of forward-swept wings. [Lawrence S Schuster; William A Lokos; Dryden Current flight test experience related to structural divergence of forward-swept wings book Research Facility.].
Krone (ref. 4) showed that divergence speeds for forward-swept wings of compos- ite materials can be increased substantially by optimally tailoring (arranging) the composite lamina thicknesses and orientations without incurring significant increases in structural mass above a so-called "strength design." As a conse.
Aeroelastic Divergence Experiments of Forward Swept Wings NASA Langley CRGIS Aeroelastic Phenomena and Related Research - Part 2 X Forward Swept Wing Performing High Angle of Attack. The present report covers the theoretical consideration of aileron reversal and wing divergence for swept wings with particular emphasis on aileron reversal of swept-back wings and examines the effects of the following parameters: the degree of sweep, wing.
inconcerning aeroelastic structural divergence for forward-swept wings, designers of high-speed air-craft were reluctant to employ forward sweep for more than two decades.
To avoid this problem, that is, to achieve sufﬁcient structural stiffness, conventional metal wing construction would have resulted in sub-stantial weight penalties.
A study has been conducted in the NASA-Langley Transonic Dynamics wind tunnel to determine the divergence characteristics of a high aspect ratio forward swept wing of Author: Stanley R. Cole. Flight testing the XA forward-swept wing aircraft has required development of new flight test techniques to accomplish subcritical extrapolations to the actual structural divergence dynamic Author: Jennifer Heeg.
10th WorldCongress on Structural and MultidisciplinaryOptimization May 19 - 24,Orlando, Florida, USA Static Aeroelastic Stiﬀness Optimization and Current flight test experience related to structural divergence of forward-swept wings book of Forward Swept Composite Wings J.K.S. Dillinger1, a2, T. Klimmek3, Z.
Gu¨rdal4 1 DLR–Institute of Aeroelasticity, Gottingen, Germany, [email protected] 2 Delft University of. X Forward Swept Wing Test Pilot Kurt Schroeder discusses program history and his experience flying the experimental aircraft.
Produced by Jarel & Betty Wheaton for Peninsula Seniors www. These increased benefits are often offset due to an increase in structural components, to overcome flutter and wing tip divergence due to high loading of the wing tips at high angles of attack. The use of composite materials and aeroelastic tailoring of the structures eliminates these instabilities without a significant increase in by: 1.
A forward swept wing configuration is considered where static divergence has to be avoided by using anisotropic properties of stiffened panels made of CFRP (carbon fibre reinforced plastic). The structural design includes parametric model generation and automated sizing of composite by: 1.
A swept wing is a wing that angles either backward or occasionally forward from its root rather than in a straight sideways direction. Swept wings have been flown since the pioneer days of aviation. Wing sweep at high speeds was first investigated in Germany as early asfinding application just before the end of the Second World has the effect of delaying the shock.
In this paper, the static aeroplastic characteristics, divergence velocity, control effectiveness and lift effectiveness are considered in obtaining an optimum weight structure. Swept wing structures are used with upper and lower skins, spar and rib thicknesses, and spar cap and vertical post cross-sectional areas as the design parameters.
The aerodynamic strip Cited by: Wing sweep is essential for airplanes which accelerate to the transonic regime and past it to the supersonic regime of flight. In the transonic regime, some surfaces of the airplane experience supersonic airspeeds, while others experience subsonic.
Divergence study of a high-aspect ratio, forward-swept wing [microform] Responsibility Airplanes > Wings > Testing. Bibliographic information. Reprint/reissue date D.C.?: National Aeronautics and Space Administration], 1 microfiche. Related Work Divergence study of a high aspect ratio, forward swept wing.
Librarian view | Catkey. due to an increase in structural components, to overcome flutter and wing tip divergence due to high loading of the wing tips at high angles of incidence , as example for X a forward swept wing flight research aircraft flight envelope was expanded to 66⁰ angle of incidence .
bending moment (WRBM) constraint are calculated. • The wing planform and thickness are held constant (outer loop MDO will treat these). • The structural constraint (WRBM) is only used to generate spanloads. • The actual wing weight is calculated using a general structural model where the spanload is one of the Size: 4MB.
stall on back swept wings, as the tips are most rearward, while delaying tip stall for forward swept wings, where the tips are forward. With both forward and back swept wings, the rear of the wing will stall first.
This creates a nose-up pressure on the aircraft. If this is not corrected by the pilot it causes the plane to pitch up,File Size: 2MB. $\begingroup$ I think one of the main drawing points for forward swept wings would be the stall characteristics.
Because of the way the air flows over the wings, the tips always stall before the root (or so I think I remember). They will also have better controllability in transonic and supersonic speed profiles.
THE NEW OPTIMALITY CRITERIA FOR STRUCTURAL DESIGN WITH CONSTRAINING ELASTIC DISPLACEMENTS (NON-COMPOSITE FORWARD SWEPT WING WITHOUT DIVERGENCE) Alexander I. Danilin*, *Samara State Aerospace University (National Research University), [email protected] Keywords: Optimality criteria, Static aeroelastic constraints.
As the wing is pushed through the air, it flexes (torsional divergence) rearward. The effect increases as air pressure and speed are increased. This change of shape of the wing typically causes the wing to become less efficient.
Most high-performance aircraft (high-speed) have wings that are swept back sharply. This reduces the effect. Title: XA Forward-Swept-Wing Flight Research Program Status Author: Gary A. Trippensee and David P. Lux Subject: H Keywords: Discrete variable camber; Flight testing; Forward-swept-wing; Instrument ation; Joint program; X A point worth mentioning is the characteristics of forward swept wings under high load factors, although the aircraft being developed is not expected to experience such forces, the wing has to be constructed with particular emphasis on eliminating the chances of structural divergence in flight.
A big benefit of swept wings is lower drag at high speed. When an aircraft with swept wings yaws, it is effectively increasing the sweep of the wing in the direction of the yaw, and decreasing the sweep of the other wing.
So the wing opposite the direction of yaw will have less sweep, therefore more drag, counteracting the yaw. Likewise, the. The story of development of the swept wing and the delta wing is long and fascinating.
Bear with me while I try to complete it in two parts. The swept wing came first. It enabled aircraft to fly near the speed of sound - “transonic speed” - and is.
This speed is called the critical Mach number. For straight wings this speed is relatively low since all the air flows over the wing. Swept wings use their shape to redirect part of the airflow along the front edge of the wing (called span wise flow), and this reduces the amount of air flowing over the wing.
This increases the critical Mach. Work at the University of Calgary has shown that the use of forward wing-sweep in OHS vehicles appears, on the basis of a simple analysis, to inhibit the well-known structural divergence problems associated with forward-swept wings on conventional, centrally tailed, by: 4.
Based on the variable forward-swept wing configuration, this paper utilized a variable forward-swept wing mechanism with a double slideways, which make it possible for the aircraft to switch among orthogonal wing, forward-swept wing and delta wing freely.
The general configuration of the variable forward-swept wing mechanism with a double slideways was elucidated by means Author: Xin Bing Su, Zhou Zhou, Xu Wang, Jing Cheng Shi, Peng Chen.
X Wings. The thin forward swept wing of NASA’s X (Figure ) can be achieved only with tailored composite wing skins. Such a wing improves maneuvering performance because the ailerons are not “washed out” by wing bending at high angles of attack as they are on rear swept wings.
which allows the wings some bending but limits. But in the end, remember that the current A is A version or depending on how you count. Airbus tossed at Airlines a number of incremental approaches.
From simply new engines on the A (A V) to new engines plus reprofiled wings (v) to the current design that stuck. They made it wider. SILVER, in Mechanics and Chemistry of Solid Propellants, In flight, the high Mach numbers generate stagnation heating conditions which are additive to those imposed by captive flight conditions.
For relatively long burning times with case-bonded motors, the interface effects caused by high temperatures, between liner, case and propellant can become very serious. This is true for all wings: those of a modern jet, wings in inverted flight, a flat plate, or a paper airplane—or, for that matter, a bird’s wing, as can be seen in the photo of a tern in.
Examples: flutter, windscreen loads (either from air loads, or requirements to withstand bird strike by a certain weight bird), wing structural divergence (usually only an issue on aircraft with forward swept wings, such as HFB), flight control hinge moments become too high for acceptable control, engine or propeller anomalies (e.g.
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Collection includes both citations and many full-text. Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C.
Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes. The issue of flight test data accuracy further complicates the comparison between wind tunnel and flight test data.
When the flight test data first arrives and the inevitable panic begins, experience shows that the flight test data system itself may be suspect, although the flight test group usually refuses to acknowledge the possibility. Mason - Transonic Aerodynamics of Airfoils and Wings (DRAFT) - Free download as PDF File .pdf), Text File .txt) or read online for free.
The book begins with two introductory chapters that address fundamental principles of aerodynamics and flight stability and form a knowledge base for the student of Aerospace Engineering. The book then covers aerodynamics of fixed wing, rotary wing and hybrid unmanned aircraft, before introducing aspects of aircraft flight stability and control.
Full text of "DTIC ADA USAF Test Pilot School. Flying Qualities Textbook, Volume 2 Part 2" See other formats.Active flutter suppression, which is a part of the group of flight vehicle technologies known as active controls, is an important contributor to the effective solution of aeroelastic instability problems when they pop up late in the development of a new aircraft or, if used from the start of the design process, it is a key element in multidisciplinary design optimization that could lead Cited by: This banner text can have markup.
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