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4 edition of Aerodynamic shape optimization of wing and wing-body configurations using control theory found in the catalog.

Aerodynamic shape optimization of wing and wing-body configurations using control theory

Aerodynamic shape optimization of wing and wing-body configurations using control theory

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Published by Research Institute for Advanced Computer Science, NASA Ames Research Center, National Technical Information Service, distributor in [Moffett Field, Calif.], [Springfield, Va .
Written in English


Edition Notes

StatementJames Reuther and Antony Jameson.
Series[NASA contractor report] -- NASA CR-198024., RIACS technical report -- 95.01., NASA contractor report -- NASA CR-198024., RIACS technical report -- TR 95-01.
ContributionsJameson, Antony., Research Institute for Advanced Computer Science (U.S.)
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17012709M
OCLC/WorldCa33153556

Fig.2 Semi-Flying-Wing Fig.3 Ho I 2 Methodologies A BWB concept was designed considering aerodynamics and structural capabilities based AERODYNAMIC PERFORMANCE OF A BLENDED-WING-BODY CONFIGURATION AIRCRAFT Toshihiro Ikeda*, Cees Bil* *The Sir Lawrence Wackett Centre for Aerospace Design Technology, RMIT. The Blended-Wing-Body (BWB) aircraft are being investigated and researched with the aim to develop more efficient aircraft configurations. The BWB configuration designates an alternative aircraft configuration where the wing and fuselage are integrated which results essentially in a hybrid flying wing shape. BWB is a hybrid of flying-. Mesh deformation schemes play an important role in numerical aerodynamic optimization. As the aerodynamic shape changes, the computational mesh must adapt to conform to the deformed geometry. This work presents an extension to an existing fast and robust radial basis function mesh movement scheme. Using a reduced set of surface points to define the mesh deformation increases the Cited by: RANS-based Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft. Title: RANS-based Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft: Publication Type: Conference Papers: Year of Publication: Authors: Lyu, Z, Martins, JRRA: Conference Name: 43rd AIAA Fluid Dynamics Conference and Exhibit.


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Aerodynamic shape optimization of wing and wing-body configurations using control theory Download PDF EPUB FB2

Aerodynamic Shape Optimization of Wing and Wing-Body Configurations Using Control Theory James Reuther and Antony Jameson The Research Institute of Advanced Computer Science is operated by Universities Space Research Association, The American City File Size: 1MB. Aerodynamic Shape Optimization of Wing and Wing-Body Configurations Using Control Theory J.

Reuther, RIACS, NASA Ames Research Center, Moffett Field, CA and A. Jam eson, Princeton University, Princeton, NJ 33rd Aerospace Sciences Meeting and Exhibit January -/ Reno, NV I.

Get this from a library. Aerodynamic shape optimization of wing and wing-body configurations using control theory. [James Reuther; Antony Jameson; Research Institute for.

Aerodynamic shape optimization of wing and wing-body configurations using control theory. AIAA paperAIAA 33rd Aerospace Sciences Cited by: Here results are presented both for the optimization of a swept wing using an analytic mapping, and for the optimization of wing and wing-body configurations using a general mesh.

View Show abstract. Surrogate-Based Aerodynamic Shape Optimization of a Wing-Body Transport Aircraft Configuration. Optimum aerodynamic design using CFD and control theory, in AIAA Paper () Aero-Elastic Multi-Point Wing Optimization Using the Coupled Adjoint Approach, New Results in Numerical and Experimental Fluid Mechanics IX, Cited by: 4.

Aerodynamic shape optimization of wing and wing-body configurations using control theory by James Reuther Published by Research Institute for Advanced Computer Science, NASA Ames Research Center, National Technical Information Service, distributor in [Moffett Field, Calif.], [Springfield, Va.

Aerodynamic Shape Optimization of the Common Research Model Wing-Body-Tail Configuration Song Chen, Zhoujie Lyuy, Gaetan K. Kenwayz, and Joaquim R. Martinsx Department of Aerospace Engineering, University of Michigan, Ann Arbor, MI Wing shape is one of the main drivers of aircraft aerodynamic performance, so most aerodynamic.

an aerodynamic optimization system for SST wing -body configuration is developed in this research. To satisfy severe tradeoff between high aerodynamic performance and low sonic boom, the present objectives are to reduceC D at a fixedC L as well as to satisfy the equivalent area distribution for low sonic boom proposed by Darden.

13 Wing shape. Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Con guration Nimeesha B. Kuntawala Masters of Applied Science Graduate Department of Aerospace Engineering University of Toronto Increasing environmental concerns and fuel prices motivate the study of alternative, un-conventional aircraft con by: 1.

16 Surrogate-Based Aerodynamic Shape Optimization of a Wing-Body IX, vol. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, ed.

by A. Dillmann, G. Heller, E. Krämer. This paper describes the implementation of optimization techniques based on control theory for wing and wing-body design of supersonic configurations. The work represents an extension of our earlier re-search in which control theory is used to devise a design procedure that significantly reduces the computational cost by employing an adjoint.

Aerodynamic optimisation has become an indispensable component for any aerodynamic design over the past 60 years, with applications to aircraft, cars, trains, bridges, wind turbines, internal pipe flows, and cavities, among others, and is thus relevant in many facets of by: Aerodynamic Optimization of Box Wing – A Case Study.

International Journal of Aviation, Aeronautics, and Aerospace, 1(4). Retrieved from The flying wing and blended wing body are two popular designs contrast to the blended wing Cited by: 1. aerodynamic shape design within the framework of the mathematical theory for the control of systems governed by partial differential equations [3].

In this view the wing is regarded as a device to pro-duce lift by controlling the flow, and its design is regarded as a problem in the optimal control of the flow equations by changing the shape of Cited by: Full text of "Aerodynamic shape optimization using control theory" See other formats.

Aerodynamic Shape Optimization of the CRM Wing using a Multilevel Approach RANS-based Aerodynamic Shape Optimization of the Blended Wing Body Aerodynamic Forces, Shape of wing and aerofoil. The preliminary results of the flow analysis and aerodynamic shape optimization of a 2-crew, passenger blended-wing-body aircraft configuration are presented.

Flow analysis is performed using an Euler-based parallel Newton-Krylov-Schur flow solver. A sequen-tial quadratic programming algorithm that allows for linear and nonlinear. Aerodynamic Shape Optimization of a Blended-Wing-Body Regional Transport for a Short Range Mission Thomas A.

Reist and David W. Zinggy Institute for Aerospace Studies, University of Toronto Du erin St., Toronto, Ontario, M3H 5T6, Canada The blended-wing-body represents a potential revolution in e cient aircraft design.

AFile Size: 8MB. recently, the method has been employed for wing design in the context of complex aircraft configurations [7], [8], using a grid perturbation technique to accommodate the geometry modifications.

Pironneau had earlier initiated studies of the use of control theory for optimum shape design of systems governed by elliptic equations [9], [10]. Dual time‐stepping schemes are recommended for the simulation of unsteady flow.

In order to realize the potential benefits of CFD, it is essential to move beyond simulation to aerodynamic (and ultimately multidisciplinary) optimization. The article concludes with a discussion of aerodynamic shape optimization via control theory. Aerodynamic optimization based on continuous adjoint method for a flexible wing is developed using FORTRAN 90 in the present work.

Aerostructural analysis is performed on the basis of high-fidelity models with Euler equations on the aerodynamic side and a linear quadrilateral shell element model on the structure side. This shell element can deal with both thin and thick shell problems with Author: Zhaoke Xu, Jian Xia.

Multilevel parametrization for aerodynamical optimization of 3D shapes. Finite Elements in Analysis and Design.

26, pp.[4]. Reuther and A. Jameson Aerodynamic shape optimization of wing and wing-body configurations using control theory. AIAA Paper. Aerospace Sciences Meeting and Exhibit. [5]. CFD algorithm for the solution of optimum aerodynamic design problems using control theory; The SYN87 code.

NLR-CR, [6] A.J. Van der Wees, J. van Muijden, and J. van der Vooren. A fast and robust viscousinviscid interaction solver for transonic flow about wing/body configurations on the bases of full potential by: 4. Computational Aerodynamics: Solvers and Shape Optimization Luigi Martinelli.

Luigi Martinelli. An Improved Method for the Aerodynamic Analysis of Wing-Body-Tail Configurations in Subsonic and Supersonic Flow. Part 1: Theory and Application Cited by: A wing-body-tail (WBT) configuration is proposed without the conventional tailplane, allowing for new requirements for the aerodynamic shape of the fuselage.

A shorter, low drag body can be employed with a deflector trailing edge (Kutta edge/KE) to modify the flow around the body so as to allow wing-body. Abstract (summary): Increasing environmental concerns and fuel prices motivate the study of alternative, unconventional aircraft configurations.

One such example is the blended-wing-body configuration, which has been shown to have several advantages over the conventional tube-and-wing aircraft by: 1.

Aerodynamic analysis of a blended-wing-body aircraft configuration Author(s) Ikeda, T: Year Abstract In recent years unconventional aircraft configurations, such as Blended-Wing-Body (BWB) aircraft, are being investigated and researched with the aim to develop more efficient aircraft configurations, in particular for very large transport.

An elementary analysis has been made of generic wing-body configurations with variable volume allotment in wing and body, for constant total useful volume, including the all-wing configuration. These aircraft were compared on the basis of the Lift-to-Drag (L/D) ratio, for specified flight by: 8.

The main purpose of the paper is to study the aerodynamic and stability characteristics of a blended-wing-body (BWB) aircraft. This paper presents the estimation and selection of aircraft design parameters, planform design, reflex airfoils, and conduct thorough stability investigation of the aircraft.

A conceptual design of BWB aircraft has been done and the design was analyzed and refined to Author: Sanjiv Paudel, Shailendra Rana, Saugat Ghimire, Kshitiz Kumar Subedi, Sudip Bhattrai.

shape optimization problems such as airfoil shape design [7,8], Multi-element airfoil shape design [9], subsonic wing shape design [10] and supersonic wing shape design [11]. The previous applications of numerical optimization methods, however, are restricted to more or less simplified problems involving not more than design Size: KB.

The blended wing-body represents a potential revolution in e cient aircraft design, yet little work has explored the applicability of this design concept to small aircraft such as those that serve regional routes.

We thus explore the optimal aerodynamic shape of both a blended wing-body and conventional tube-and-wing regional aircraft through Cited by: 5.

This paper presents an adjoint optimization technique and its application to the design of a transonic turbine cascade. Capable of a quick and exact sensitivity analysis and using little computational resources, the adjoint method has been a focus of Cited by: This work covers a contribution to two most interesting research fields in aerodynamics, the finite element analysis of high-speed compressible flows (Part I) and aerodynamic shape optimization (Part II).The first part of this study aims at the development of a new stabilization formulation based on the Finite Increment Calculus (FIC) scheme for the Euler and Navier-Stokes equations in the Author: M.

Kouhi, E. Oñate, G. Bugeda. T he preliminary results of the ow analysis and aerodynamic shape optimization of a 2-crew, passenger blended-wing-body aircraft conguration are presented. Flow analysis is performed using an Euler-based parallel Newton-K rylov-Schur ow solver.

A sequen-tial quadratic programming algorithm that allows for linear and nonlinear constraints is. JiméNez-Varona, J., Design of blended-wing-body configurations using a constrained numerical optimisation method,CEAS/KATnet Conference on Key Aerodynamic Technologies, Bremen, Germany, June Cited by: a blended wing body transport with a number of constraints.

The wing shape design is done by splitting the problem into 2D airfoil design and 3D twist optimization with a frozen planform. A 45% to 50% reduction of inviscid drag is nally obtained, with desired pitching moment. The results indicate that further improvement can be obtained by.

use for design of race car to control it at high speed. Normally, the wing of WIG crafts should have as flat as possible and positive of angle of attack [1]. Several initial experimental and computational techniques to calculate the lift by special shape of the body in ground proximity can be found in the references [].

A Low Subsonic Study of the NASA N2A Hybrid Wing-Body Using an Inviscid Euler-Adjoint Solver. Dan Almosnino Roll Control Evaluation of the XA Flying Wing Aircraft Using Active Camber Control compared to Conventional Ailerons using Vortex Lattice Theory Trajectory and Aerodynamic Control Optimization of Civil Aircraft Descent Under.

The aerodynamic shape optimization design system was established in this paper. In the system, the RANS equation was used for solving the flowing; the free form deformation (FFD) method was used for the geometry parameterization, and the genetic algorithm was used for the optimization search.

For the reducing of the time cost, the Kriging model was used for the surrogate model instead Cited by: 1. Stability and Control Estimating Aerodynamic Properties A necessary ingredient for determining the aerodynamic properties of an aircraft is to be able to determine the aerodynamic properties of parts of the aircraft.

If we look at the expression for the pitch-moment curve slope, we can see some of the parameters that need to be estimated: (1)File Size: KB.Similarly, a general supersonic program was developed for numerical analysis of the aerodynamic characteristics of a thin wing.

The theory was extended to include wing-body interferences. This extended treatment consists of slender body theory combined with a thin wing solution using a "characteristic box" method for supersonic analysis.conventional design has been estimated for the blended wing body aircraft.

However, these benefits can only be realized as an aerodynamic shape design. Unfortunately, little is known regarding the best aerodynamic shape for BWB due to a large number of extra design variables and stronger coupling with theFile Size: 1MB.