4 edition of Supersonic wing and wing-body shape optimization using an adjoint formulation found in the catalog.
Supersonic wing and wing-body shape optimization using an adjoint formulation
1995 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
|Other titles||Supersonic wing and wing body shape optimization using an adjoint formulation.|
|Statement||James Reuther and Antony Jameson.|
|Series||[NASA contractor report] -- NASA CR-199150., RIACS technical report -- 95.14., NASA contractor report -- NASA CR-199150., RIACS technical report -- TR 95-14.|
|Contributions||Jameson, Antony, 1934-, Research Institute for Advanced Computer Science (U.S.)|
|The Physical Object|
Texts / References Bannantine J.A., Comer J.J., Handrock J.L., Fundamentals of Metal Fatigue Analysis, Prentice Hall Inc. Rao S.S., Reliability Based Design, McGraw Hill Inc., A. Mubeen, Machine Design, Khanna Publishers, AE Aerodynamic Design of Compressors and Turbines 3 0 0 6 Axial Flow Compressor: Work done, Pressure. FROST, D.L. Refereed Conference Proceedings. Frost, D.L., Goroshin, S., Levine, J., Ripley, R., and Zhang, F., , “Critical Conditions for Ignition of Aluminum. Aiaa Mdo Tc White Paper on Mdo. The Challenge and Promise of Blended-Wing-Body Optimization, Sean Wakayama (Boeing) and Ilan Kroo (Stanford). the flight shape of the wing should have minimum aerodynamic drag and sufficient effectiveness for all configurations. Despite all these design criteria in a wide range of applications the.
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Get this from a library. Supersonic wing and wing-body shape optimization using an adjoint formulation. [James Reuther; Antony Jameson; Research Institute for Advanced Computer Science (U.S.)].
Wing flap deflection angles of a supersonic transport are optimized to improve transonic cruise performance.
Toward this end, a numerical optimization method is adopted using a three-dimensional. Fuselage Shape Optimization of a Wing Body Configuration with Nacelles the action of an engine nacelle upon a wing in supersonic flow. developed by using a parallel continuous adjoint.
Reuther and A. Jameson. Supersonic wing and wing-body shape optimization using an adjoint formulation. Technical report, The Forum on CFD for Design and Optimization, (IMECE 95), San Francisco, California, November Google ScholarCited by: 2.
Jameson S. Nadarajah and J.J. Alonso. Sonic boom reduction using an adjoint method for wing-body configurations in supersonic flow.
AIAA paper9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization Conference, Atlanta, GA, September Google ScholarCited by: Direct Method for Optimization of a Centrifugal Compressor Vaneless Diffuser The Direct Method for Optimization achieves a final shape from maximizing/minimizing a nonlinear function, i.e., the objective function.
“Supersonic Wing and Wing-Body Shape Optimization using an Adjoint Formulation,” CFD for Design and Optimization Cited by: Computational Aerodynamics: Solvers and Shape Optimization Luigi Martinelli.
Luigi Martinelli. Generation of Boundary-Conforming Grids Around Wing-Body Configurations Using Transfinite Interpolation,” Constrained Multipoint Aerodynamic Shape Optimization Using an Adjoint Formulation and Parallel Computers,”Cited by: Full text of "Aerodynamic shape optimization using control theory" See other formats.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Tremendous progress has been achieved in the area of ASO (Aerodynamic Shape Optimization) such as airfoil and wing/body design in transonic flow regime.
For a large num- ber of design variables, GBOM (Gradient Based Optimization Method) using adjoint approach is very popular because of its computational efficiency [3,4,11,15,20].Cited by: State-of-the-art in aerodynamic shape optimisation methods.
Author links open overlay panel S.N Their result showed that coupling stability constraint sensitivities into the adjoint formulation had a significant impact on optimal wing shape.
Both the subsonic wing and blended-wing body optimisation present mildly multi-modal problems in 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. 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. 12 April - 15 April Orlando, Florida Mathematical Formulation for Deployment Dynamics of Shape Memory Polymer Composite Space Structures.
Supersonic Wing Box Weight Optimization Using Curvilinear Spars and Ribs. Davide Locatelli. The conference was organised around a number of parallel symposia, regular sessions, and keynote lectures focused on surrogate-based optimization in aerodynamic design, adjoint methods for steady & unsteady optimization, multi-disciplinary design optimization, holistic optimization in marine design, game strategies combined with evolutionary.
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.
performance of a blended wing body aircraft, Journal of Aerospace Engineering, Vol,pp A Le Moigne, N Qin, Airfoil profile and sweep optimization for a blended wing-body aircraft using a discrete adjoint method, The Aeronautical J, Vol, No., pp The optimization techniques presently employed in the design methods are of the “search” type, and do not employ any of the elements of calculus of variations in order to obtain the maxima.
Although an entire book (Ref. 5) has been devoted to aerodynamic optimization using. Abu-Zurayk M, Brezillon J () Shape optimization using the aerostructural coupled adjoint approach for viscous flows.
In: Evolutionary and deterministic methods for design, optimization and control, by: Interactive Inverse Design Optimization of Fuselage Shape for Low-Boom Supersonic Concepts Li, W.
/ Shields, E. / Le, D. / American Institute of Aeronautics and Astronautics | print version. Siouris S & Qin N () Study of the effects of wing sweep on the aerodynamic performance of a blended wing body aircraft.
P I MECH ENG G-J AER, (G1), Le Moigne A & Qin N () Aerofoil profile and sweep optimisation for a blended wing-body aircraft using a discrete adjoint method. AERONAUT J, (), Leoviriyakit K, Kim S, Jameson A () Aero-structural wing planform optimization using the Navier-Stokes equations.
In: 10th AIAA/ISSMO multidisciplinary analysis and optimization conference, Albany, AIAA Google Scholar; Lyu Z, Martins JRRA () Aerodynamic shape optimization studies of a blended-wing-body aircraft. Development of the Nano Hummingbird: A Tailless Flapping Wing Micro Air Vehicle Constrained Adjoint-Based Aerodynamic Shape Optimization in a Multistage Turbomachinery Environment.
Walther, Improved Aerodynamic Analysis for Hybrid Wing Body Conceptual Design Optimization. Gern, F. / American Institute of Aeronautics and Astronautics.
A, “Two-Level Composite Wing Structural Optimization Using Response Surfaces “, Proceeding of First ASMO UK / ISSMO conference on Engineering Design Optimization, Ilkley, West Yorkshire, UK, July 8.
Lyu and Martins, J. A., “ RANS-based Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft ”, in 43rd AIAA Fluid Dynamics Conference and Exhibit, Google Scholar BibTeX. Aerodynamic Optimization of Car Shapes using the Continuous Adjoint Method and an RBF Morpher, by E.M.
Papoutsis-Kiachagias, S. Porziani, C. Groth, M.E. Biancolini, E. Costa and K.C. Giannakoglou.- 4. Holistic Optimization in Marine Design.- Upfront CAD --Parametric modeling techniques for shape optimization, by S.
Harries, C. Abt and M. A SQP Algorithm for Large-Scale Constrained Optimization: SNOPT. () Coupled adjoint aerostructural wing optimization using quasi-three-dimensional aerodynamic analysis. () Aerodynamic Shape Optimization of a Blended-Wing-Body Regional Transport for a Cited by: RANS-Based Aerodynamic Shape Optimization of a Strut-Braced Wing with Overset Meshes View Section, An Adaptive Constraint Tolerance Method for Optimization Algorithms Based on the Discrete Adjoint Method.
IUTAM Symposium on Transsonicum IV, Göttingen, Germany, September 02 – 06, Transonic Wing Shape Optimization Using a Genetic Algorithm Jameson, A.: Optimum Transonic Wing Design Using Control Theory Lutz Boom Reduction Using an Adjoint Method for Supersonic Transport Wing-Body Configurations.
Real gas effects Multiphase. Aerodynamic Design & Optimization Ideen Sadrehaghighi, Ph.D. Optimized Baseline Figure Aerodynamic Shape Optimization Procedure using Adjoint Variable as Sensitivity Analysis. Figure Pressure Contours. Figure General Description of Computational Planes.
Figure Turbomachine Design Process. () Aerodynamic shape optimization of wind turbine blades using a Reynolds-averaged Navier-Stokes model and an adjoint method.
Wind Energy() A pseudospectral method for solving optimal control problem of a hybrid tracked by: B. Brelje, J. Anibal, A. Yildirim, C. Mader, and J. Martins. Flexible Formulation of Spatial Integration Constraints in Aerodynamic Shape Optimization. The adjoint solver is further utilized to set up an airfoil shape optimization framework in Python and demonstrated for an airfoil shape optimization inverse problem.
The two-dimensional adjoint Euler solver is extended to incorporate GPU acceleration using Compute Unified Device Architecture (CUDA) kernels and named ADjoint-GARfield (ADGAR). Admitting the Inadmissible_ Adjoint Formulation for Incomplete Cost Functionals in Aerodynamic Aerodynamic Assessment of Flight- Determined Subsonic Lift and Drag Characteristics of Seven Lifting-Body and Wing-Body Reentry Vehicle Business Jet Wing Design Using _Aerodynamic Shape Proceedings of the NASA Langley workshop on numerical grid generation techniques, Langley, VA, October, Caughey DA, “A systematic procedure for generating useful conformal mappings”, Int J Num Meth Eng Eriksson LE,”Generation of boundary-conforming grids around wing-body configurations using transfinite interpolation”, AIAA.
Aviation researchers are increasingly focusing on unconventional vehicle designs with tightly integrated propulsion systems to improve overall aircraft performance and reduce environmental impact.
Properly analyzing these types of vehicle and propulsion systems requires multidisciplinary models that include many design variables and physics-based analysis tools. This need poses a challenge Author: Eric S. Hendricks, Justin S. Gray. Shock-Induced Flow Separation in an Overexpanded Supersonic Planar Nozzle.
Authors: B. Zebiri, A. Piquet, A. Hadjadj, S. Verma Pages: 1 - 10 Abstract: AIAA Journal, Ahead of Print. Citation: AIAA Journal PubDate: TZ DOI: /1.J ; Cross Validation of Aerodynamic Shape Optimization Methodologies for Aircraft Wing. This research is concerned with the design of adaptive structures for achieving global multi-shape morphing aerodynamic configurations, by using slender structures.
The proposed methodologies pursue two threads towards global optimisation of morphing structures, by providing means of aerodynamic enhancement, using efficient structural shape Author: Narcis M.
Ursache. تحميل (28):: Aerodynamic shape optimization by multi-fidelity modeling and manifold mapping رسالة ماجستير تحميل (29):: Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomenaرسالة دكتوراه.
In case an implicit or discrete adjoint formulation is chosen to solve a problem, one can chose two linear solvers. I had this situation long ago with the 2nd-order Roe scheme for the viscous or inviscid flow around a wing, wing-body or airfoils using the Fluent. Any having shape optimization cfg file or please tell me how to do shape.
This book will be useful for scientists and engineers who are looking for efficient numerical methods for PDE-constrained optimization problems. It will be helpful for graduate and Ph.D.
students in applied mathematics, aerospace engineering, mechanical engineering, civil engineering and computational engineering during their training and research. Raymond L. Barger, A Method for Designing Blended Wing-Body Configurations for Low Wave Drag, NASA TP, Septemberpp.
Lance B. Bush, Resit Unal, Lawrence F. Rowell and John J. Rehder, Weight Optimization of an Aerobrake Structural Concept for a Lunar Transfer Vehicle, NASA TP, Decemberpp. Based on our previous experience developing an unsteady RANS-FWH (Ffowcs Williams-Hawkings) far-field acoustic optimization capability, the Phase 1 proposal targets the formulation of the turbulence noise source terms used by the JeNo code, along with the discrete adjoint of these terms within an existing adjoint-enabled RANS solver.Flight Dynamics Principles its location on the mac of a wing and is also used extensively for locating the ac on the mac of a wing–body combination without too much loss of validity.
It should be appreciated that the complex aerodynamics of a wing and body combination might result in an ac location which is not at the quarter chord point.