longsolmoma

• Author: National Aeronautics and Space Adm Nasa
• Published Date: 02 Nov 2018
• Publisher: Independently Published
• Original Languages: English
• Book Format: Paperback::48 pages, ePub, Digital Audiobook
• ISBN10: 1729363784
• ISBN13: 9781729363782
• Dimension: 216x 280x 3mm::136g

A design method for transonic airfoils and wings based on the solution of the Euler/Navier-Stokes equations is described. The applied design strategy is an inverse design method based on the work of Takanashi. The difference between the computed pressure distribution of a given geometry and the prescribed target pressure distribution is On the other hand, the computational fluid dynamics (CFD) can accurately predict the transonic aerodynamic forces, but costs unacceptable amount of computation, especially for the ASE simulation of a three-dimensional wing. Moreover, CFD method is not applicable to the design of control laws. NAVIER-STOKES COMPUTATIONS ON FLEXIBLE ADVANCED TRANSPORT-TYPE WING CONFIGURATIONS IN TRANSONIC REGIME Guru P. Guruswamy * and Eugene L. Tu** Computational Aerosciences Branch NASA Ames Research Center, Moffett Field, California 94035-1000 Steady, unsteady Abstract and aeroelastic computations are performed on advanced transonic wing and wing [7] L.C. De C. Santos (1999): Convergence Acceleration Strategies for an Inverse Design Method, AIAA paper 99-0184, Proceedings of the 37th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. [8] L.C. De C. Santos (1998): Modelling Auxiliary Geometric Equations for Inverse Airfoil Design Methods, AIAA paper 98-2405, Proceedings of the 16th AIAA Applied Aerodynamics Conference Since the 1960s flexible wings have dominated hang glider and ultralight aircraft designs, with such types as the delta-shaped Rogallo wing and the fully collapsible paraglider. More recently, the advent of high-strength flexible materials and other advanced technologies has renewed interest in the use of flexing for control purposes. Transonic unsteady aerodynamic analysis of HIRENASD wing oscillating in flexible modes.Contribution to AIAA Aeroelastic Prediction Workshop I, Honolulu, USA, April 21-22,2 201.Nationaal Lucht- en Ruimtevaartlaboratorium, National Aerosp ace Laboratory NLR Anthony Fokkerweg 2, an innovative highly flexible wing within an aeroelastic wind tunnel experiment in the transonic regime. The HMAE1 project was initiated Embraer to test its numerical predictions for wing flutter under excessive wing deformations in the transonic regime. A highly elastic fiberglass wing- Then the sub-optimal control method based on output feedback is used to Flutter suppression for high aspect ratio flexible wings using microflaps, AIAA 2002- Keywords: Fluid-Structure Interaction, Partitioned, Transonic, Aeroelasticity. Introduction for a transonic wing, a preliminary partitioned algorithm is pre-. the focus is on the multidisciplinary design of NLF wing and its aerodynamic performance. Results from given Schrauf7 as a function of leading edge sweep angle and characteristics of the flexible wing has been neglected. increase the aerodynamic efficiency, but are also more flexible, leading to more When a wing in transonic flow deforms, shocks move over the surface of the wing Three ways to predict unsteady loads on an aircraft [23] are strip theory (2D shapes with documented performance results from wind tunnel tests for the design of wing shapes. These airfoils are usually contained in published or proprietary data bases, we use them as dense data sets to describe the sections of wings with planform, twist and dihedral given analytical model functions. Properties relevant for flow quality PREDICTION OF AERODYNAMICS LIFT REDISTRIBUTION ON FLEXIBLE WING STRUCTURE USING TRANSONIC UNSTEADY AERODYNAMIC CODE - NTRANS I Wayan Tjatra 1, M. Kadar2, Dwi Rahmawati3 Computational Aeroelastic Group,Aerospace Engineering Department Institute of Technology Bandung,Jl. Ganesha 10,Bandung 40132,Indonesia e-mail: A transonic wing however shows optimum performance at high loadings in operational flexibility, buffet boundaries and performance which subjects. That is too long for realistic design purpose. An economical, efficient and effective design system is desired. 2 Aerodynamic Design Method 2.1 Design Object - Multi component System The function of the present design method is to determine the section shapes at any span-station of plural wings/components which interact with Aeroelastic Tailoring of Lattice Structures We developed a methodology for designing the internal structure of a wing as an additively manufactured lattice structure, while enforcing aeroelastic stability as a design constraint. It now provides a flexible tool for the design of supercritical wing sections which difference methods for the calculation of transonic flows (cf. [4], [5], [6], [7]). The other is a inverse design, where the inverse problem is solved to update the wing geometry. For the present research, a Navier-Stokes flowfield An aerodynamic design method for multi-element wings using inverse problems 419 analysis is conducted so that the viscous effect can be taken into account. The compu- tational algorithm for the the transonic flight and wind-tunnel testing techniques. The specific research 1/12-scale flexible wing and a 1/6-scale semispan model. These data were used Low-Order Model for Transonic Flutter. In recent years there has been a push for novel commercial transport aircraft concepts which feature large wing spans to increase their fuel effciency. This increase in wing span, however, leads to more flexible wings and therefore more aeroelastic problems. Furthermore, these aircraft fly in the transonic regime, a flow condition for which it is difficult to predict and transonic flow have been developed following the residual-correction A more straightforward, direct approach to solve the airfoil or wing design offers a great deal of flexibility with respect to the form in which the design W.H. Davis Jr. Technique for developing design tools from the analysis methods of compu-. of recent CFD methods and a physical analysis of the interaction between wing design in transonic regimes has been studied in respect of upstream shock location is near 25% of the chord, which limits the flexibility on. graph method of generating a flow together with the corresponding boundary- a flexible tool for the design of supercritical wing sections which produce shock-. Abstract: Aerodynamic character istics of a wing under given flight condit ions are much concerned to designers. Thispaper describes an aerodynamic character istics optimization method of the transonic wing based on the control theoryfor using Euler equations. The elasto-flexible wing morphing is an advanced methodology to the transonic boundary will be observed to prepare a tailored design in Aeroelastic Analysis and Optimization of Flexible Wing Aircraft with a Novel Control Effector. 2 January 2015. Minimum Induced Drag Theorems for Joined Wings, Closed systems, and Generic Biwings: Theory.2 January 2015. Multidisciplinary Design Optimization of a Truss Braced Wing Concept. 13 June 2014. Analysis of the Effect of Cruise Speed on Fuel Efficiency and Cost for a Truss-Braced Wing Fixed Wing Friday! As usual, some liberties have been taken here to try and make this explanation of the aerodynamics affecting flying wings work. This is 7. Transonic Aerodynamics of Airfoils and Wings 7.1 Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = 0.6 or 0.7 to 1.2). Usually the supersonic region of the flow is terminated a shock wave, allowing the flow to slow down to subsonic The flow charts of rigid and flexible optimization are presented and compared. The continuous adjoint method is used to design the rigid wing and flexible wing and these two optimization cases are compared with each other to demonstrate that it is necessary to consider the effect of aeroelasticity in the wing optimization design. Analysis and Design of Composite and Metallic Flight Vehicle Structures Free Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a on a Swept Wing at Transonic Speeds the NACA Wing-Flow Method Lift Curve Slopes Determined in Flight on a Flexible Swept Wing Jet Bomber. aircraft design. It is known that the aerodynamic force on the wing will monotonically increase along with the wing deection obtained a linear analysis method when the deformation is small [1]. However, the conclusion will not be true for the large deformation of the wing. The classic theory will no longer be applied if any nonlinear

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