3 edition of Navier-Stokes computations on full wing-body configuration with oscillating control surfaces found in the catalog.
Navier-Stokes computations on full wing-body configuration with oscillating control surfaces
by American Institute of Aeronautics and Astronautics, [National Aeronautics and Space Administration, National Technical Information Service, distributor in Washington, DC, Springfield, Va
Written in English
|Other titles||Navier Stokes computations on full wing body configuration with oscillating control surfaces|
|Statement||Shigeru Obayashi, Ing-Tsau Chiu, Guru P. Guruswamy.|
|Series||NASA technical memorandum -- 207298|
|Contributions||Chiu, Ing-Tsau., Guruswamy, Guru P., United States. National Aeronautics and Space Administration.|
|The Physical Object|
The maneuverability of the Sukhoi Su at very high angles of attack (AoA) was remarkably appealing. Canard angle, in cooperation with aircraft wing, created a flow pattern whereby, in that position, the fighter still had as much lifting force as possible in order not to stall. The behavior of changing canard angle configuration played an essential role in creating the strong vortex core Author: Sutrisno, Tri Agung Rohmat, Setyawan Bekti Wibowo, Sigit Iswahyudi. Supersonic diffusers. See also what's at your library, or elsewhere.. Broader term: Aerodynamics, Supersonic; Filed under: Supersonic diffusers Performance of a short annular dump diffuser using suction-stabilized vortices at inlet Mach numbers to / (Washington: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.
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Of the code has further been extended to handle a full-span wing-body configuration with control surfaces. This article reports the results of unsteady Navier-Stokes simulations of transonic flows over a rigid arrow-wing body configuration with oscillating control surfaces.
Computations have been made with and without control surface deflections. Get this from a library. Navier-Stokes computations on full wing-body configuration with oscillating control surfaces. [Shigeru Obayashi; Ing-Tsau Chiu; Guru P Guruswamy; United States.
National Aeronautics and Space Administration.]. Virtual Zone Navier-Stokes Computations of Oscillating Control Surfaces Another area of effort conducted during the past year was to implement the virtual zone concept into a time accurate finite difference code, ENSAERO (ref.
7), for application to an oscillating control surface mounted on a clipped delta wing at transonic Size: 5MB. Grid movements for control surfaces are defined through a separate module, which is driven by an external grid generation tool. Results are demonstrated for a wing with a part-span control surface.
Grids for the test case are determined from detailed grid sensitivity studies based on both nonoscillating and oscillating by: 3. Navier-Stokes Computations of Longitudinal Forces and Moments for a Blended Wing Body S.
Paul Pao∗, The placement of control surfaces and the interactions between them may be very different from that different scale wind tunnel models of an early Boeing blended wing body conﬁguration have been used in tunnel tests: a. and aeroelastic computations are performed on advanced transonic wing and wing-body configurations.
The flow is modeled by the Navier- Stokes equations and structures for aeroelastic com- putations are modeled by the modal equations. The inadequacy of Euler equations and importance of us- ing the Navier-Stokes equations with turbulence model is.
Abstract. The progress made in multidisciplinary computations using high-fidelity flow and structural equation is summarized. Given the power of super computers it has been demonstrated that it is practical to use high fidelity equations to accurately model aeroelasticity associated with complex flows involving shock-waves, vortices and : Guru P.
Guruswamy. Survey of Computational Method A survey of the computational technique used to solve the Navier-Stokes equations is given in the following slides describing DFS as Direct Finite Element Simulation: Adaptive Finite Element Method for Navier-Stokes with Slip with some glimpses here: Airflow interacting with vocal chords Airflow around a car Bloodflow in heart Flow around.
Summary. A set of 3D Navier-Stokes solutions around a complete wing-body-tail configuration is presented for different mesh resolutions. The local mesh dependent behaviour is investigated and from these experiences, a technique is derived that aims for multi-sweep y + driven mesh adaptation to wing- and fuselage boundary layer profiles.
This technique is described and Author: E. Elsholz, H. Steinmeyer, D. John. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A set of aerodynamic coefficients and static stability derivatives of the wing-body-tail model at low Mach number of have been computed using Reynold's Averaged Navier-Stokes CFD.
Static flexible computation. Aeroelastic computations of flexible configurations 23 Moo = Q = 37 psf PRESENT STUDY (FULL POTENTIAL/^ AEROELASTIC CODE) TEST DATA I CONTROL SURFACES DEFLECTION Cited by: Insights and lessons learned from the aerodynamic analysis of a High Wing Transport high-lift configuration are presented.
Three-dimensional Navier. This page in the original is blank. A fully elliptic numerical method for the solution of the Reynolds Averaged Navier Stokes Equations is applied to the flow around the HSVA Tanker. The weaknesses of the simulation are analysed by comparing several discretisation schemes and grids as well as.
At the AIAA CFD drag prediction workshop inthe DLR-F4 wing-body configuration was computed using 14 different codes from all over the world, and 35 solutions were provided for the condition with C L =, M ∞ = The standard deviation of the CFD solutions was approximately 20 drag counts, compared to 5 drag counts for the wind Cited by: part of the Navier-Stokes spatial operator is driven by the following requirements: 1.
Applicability to 3-D reasonably smooth grids not necessarily deﬁned by mapping function(s), but rather by a set of vertices. Applicability to high aspect ratio grids typi-cal of the Navier-Stokes computations. Ability“to coexist" with viscous terms. Navier-Stokes Computations on Full Wing-Body Configuration with Oscillating Control Surfaces Author(s): Obayashi, 8 Technical Paper Euler/Navier-Stokes flow computations on flexible configurations for stability analysis.
Guruswamy, G., Tu, E. Optimum Aerodynamic Design Using the Navier–Stokes Equations two or more to resolve the boundary layer. Second, there is the additional cost of computing the viscous terms and a turbulence model.
Finally, Navier–Stokes calculations generally converge much more slowly. parallelisation of the ﬂow and adjoint solvers with OpenMP. A three-dimensional Navier-Stokes optimisation of the ONERA M6 wing is presented. After describing the concept of Blended Wing-Body and the studies carried out on this aircraft, several aerodynamic optimisations are performed on this geometry with the capability developed in this.
"A Navier-Stokes/Full Potential/Free Wake Method for Advancing Multi-bladed rotors," Proceedings of the AHS Forum, April May 1,pp. Tapia, F., Schrage, D.
and Sankar, L. N., "Inclusion of Viscous Effects to an Aerodynamic Design Method for Rotor Blades," Proceedings of the Proceedings of the AHS Forum, April May 1. The first Navier-Stokes computations can be credited to Briley and McDonald who used a linearized block implicit scheme with an ADI-type splitting in order to solve at low Mach numbers the compressible Navier-Stokes equations for a laminar horseshoe root vortex created by the intersection of an elliptic strut and a flat plate.Full text of "Surface Modeling, Grid Generation, and Related Issues in Computational Fluid Dynamic (CFD) Solutions" See other formats.Full text of "Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.