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|
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.