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Friday, July 31, 2020 | History

3 edition of Subsonic wing optimization for handling qualities using ACSYNT found in the catalog.

Subsonic wing optimization for handling qualities using ACSYNT

Subsonic wing optimization for handling qualities using ACSYNT

final report, MS thesis : NASA grant number NCC 2-855, Cal Poly project 5339

  • 301 Want to read
  • 10 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Computer aided design.,
  • Aircraft stability.,
  • Aerodynamic stability.,
  • Applications programs (Computers),
  • Vortex lattice method.,
  • Three dimensional models.

  • Edition Notes

    StatementDani Soban, [principal investigator], Daniel J. Biezad.
    Series[NASA contractor report] -- NASA-CR-202405., NASA contractor report -- NASA CR-202405.
    ContributionsBiezad, Daniel J., 1944-, United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15507258M

    texts All Books All Texts latest This Just In Smithsonian Libraries FEDLINK (US) Genealogy Lincoln Collection. National Emergency Library. Top American Libraries Canadian Libraries Universal Library Community Texts Project Gutenberg Biodiversity Heritage Library Children's Library. Open Library. Aircraft performance can be optimized at the flight condition by using available redundancy among actuators. Effective use of this potential allows improved performance beyond limits imposed by design compromises. Optimization based on nominal models does not result in the best performance of the actual aircraft at the actual flight condition.

    The analysis functionality of the AV design is integrated with a Genetic Algorithm (GA) to form an integrated Multi-disciplinary Design Optimization (MDO) methodology for optimal AV design synthesis. This research fills the gap in integrated subsonic fixed-wing UAV AV MDO methods. Subsonic Fixed Wing Project. Dr. Rubén Del Rosario, Project Manager Dr. Rich Wahls, Project Scientist Mr. Greg Follen, Deputy Project Manager Dr. Nateri Madavan, Deputy Project Scientist. Technical Conference NASA Fundamental Aeronautics Program Subsonic Fixed Wing Project Cleveland, OH, March 15 - 17,

    Optimization of Subsonic and Transonic Airfoils for Natural Laminar Flow using a Discrete-Adjoint Method Abstract The design of Natural Laminar Flow (NLF) airfoils at subsonic and transonic speeds is demonstrated by high-fidelity multipoint aerodynamic shape optimization capable of efficiently incorporating and exploiting. An improved method is presented for estimating the subsonic location of the semispan aerodynamic center of a swept wing and the aerodynamic moment components about that aerodynamic center. The method applies to wings with constant linear taper and constant quarter-chord sweep. The results of a computational fluid dynamics study for wings.


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Subsonic wing optimization for handling qualities using ACSYNT Download PDF EPUB FB2

An illustration of an open book. Books. An illustration of two cells of a film strip. Video An illustration of an audio speaker. Subsonic wing optimization for handling qualities using ACSYNT book Wing Optimization for Handling Qualities using ACSYNT Item Preview remove-circle Subsonic Wing Optimization for Handling Qualities using ACSYNT by Soban, Danielle Suzann.

Publication date Subsonic wing optimization for handling qualities using ACSYNT: final report, MS thesis: NASA grant number NCCCal Poly project Author: Dani Soban ; Daniel J Biezad ; United States. Subsonic Wing Optimization for Handling Qualities Using ACSYNT.

calculation of a longitudinal handling qualities metric, and inherent methodology to optimize a given aircraft configuration for longitudinal handling qualities, including an intuitive graphical interface. The PREDAVOR tool may be applied to both subsonic and supersonic Author: Danielle Suzanne Soban.

Although the overall appearance of modern airliners has not changed a lot since the introduction of jetliners in the s, their safety, efficiency and environmental friendliness have improved considerably. Main contributors to this have been gas turbine engine technology, advanced materials, computational aerodynamics, advanced structural analysis and on-board systems.

Since aircraft Author: Egbert Torenbeek. COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle coronavirus.

Multi-Disciplinary Design Optimization of Subsonic Fixed-Wing Unmanned Aerial Vehicles Projected Through John F. Gundlach Abstract Through this research, a robust aircraft design methodology is developed for analysis and optimization of the Air Vehicle.

the wing. Formal aerostructural optimization, spread over a collection of realistic load cases and flight metrics, is the best way to exploit the fundamental conflict between wing weight and aeroelastic performance.

Wing structural configurations that have been recently enabled by advances in manufacturing and materials are one focus of this paper. Integrated Design and Control of a Flying Wing Using Nonsmooth Optimization Techniques. Authors; Authors and affiliations; Yann Denieul; Design of the blended-wing body subsonic transport.

von Karman Institute for Fluid Dynamics () Handling qualities of the airbus flying wing resolution. The Flight-Optimization-System (FLOPS) code encountered difficulty in analyzing a subsonic aircraft.

The limitation made the design optimization problematic. The deficiencies have been alleviated through use of neural network and regression approximations.

The insight gained from using the approximators is discussed in this paper. The use of a transonic airfoil code for analysis, inverse designand direct optimization of an airfoil immersed in propfan slipstream is described.

The thin airfoil blade is designed and calculated by blade element and momentum theory. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA   One of Torenbeek's earlier books, "Synthesis of Subsonic Airplane Design", published inis an essential reference book for designers of transport-category subsonic aircraft (i.e., airliners).

An update would have been useful, but this is not it. This book concentrates more on design methodology and, in particular, design s: 8. Subsonic Aerodynamics of Airfoils and Wings Introduction In this chapter we discuss the subsonic aerodynamics of airfoils and wings.

We look at the basic aerodynamics mainly from an inviscid point of view. Generally, this is a reasonable starting point for thinking about aerodynamics in attached flow. Traditionally, the methods used to make. Modification of ACSYNT aircraft computer program for preliminary design semi-annual progress report, October - March Moffett Field, CA: [Washington, DC: Springfield, Va: NASA Ames Research Center ; National Aeronautics and Space Administration ; National Technical Information Service, distributor.

MLA Citation. The optimal shape of flying wings for subsonic and transonic speeds is examined using a suite of tools developed around a three-dimensional, time-spectral, Euler computational fluid dynamics solver. The first result in the study is a lift-constrained drag minimization, performed on an unswept, rectangular wing.

Secondly, an outboard wing section normal to the subsonic portion of the leading edge, which had a high normal angle-of attack, was considered. The optimization resulted in a shape with twist and camber that eliminated the adverse pressure gradient, hence, exploiting the leading-edge thrust.

It is shown that the gull-wing configuration promises to have satisfactory handling qualities for a region of center of gravity locations, for which good Oswald efficiency can also be achieved. We use cookies to make interactions with our website easy and meaningful, to better understand the use of our services, and to tailor advertising.

For further information, including about cookie. The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs.

At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities.

Let's use a wing to help get a better understanding of lift at subsonic speeds. With a typical subsonic wing, the upper surface is more curved than the lower surface. The curved upper surface constricts the flow of air more than the flatter lower surface, causing the air above the wing. A numerical and analytical solution of the problem of designing a two-element wing airfoil providing maximum lift-drag ratio in a subsonic viscous flow is presented.

In order to bring the theoretical results closer to the facts, viscosity and compressibility are taken into account within the framework of boundary layer theory and the Chaplygin gas model, respectively.Using this framework, Freedom Fighter's wing is optimized; the comparison of the optimized wing with its original design is shown in Fig.

4. The work of EBF3PanelOpt is funded under NASA Subsonic Fixed Wing Hybrid Body Technologies NRA Contract (NASA NNL08AA02C) with Ms. Karen M. Brown Taminger as the API and COTR and Richard Keith Bird as the.Numerical optimization design of a flying vehicle remans a difficult task.

Investigations are performed for single crucial elements. In case of a supersonic civil airplane such element is the wing that carryes main part of aerodynamic loading. There are two statements of the problem, optimization of the isolated wing and the wing of airplane.