Advances in overset CFD processes applied to subsonic high-lift aircraft

Rogers, Stuart E.; Roth, Karlin R.; Nash, Steven M.; Baker, Mel; Slotnick, Jeffrey P.; Whitlock, Mark; Cao, Hoa V.

doi:10.2514/6.2000-4216

Cited by 44 publications

(15 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Another methodology that lends itself to the solution of complicated flow problems is the overset, or chimera, structured grid method. The flow solver OVERFLOW is based on this approach and Rogers et al [79,80,68,70,69] have applied it to obtain flow simulations for several high-lift configurations including an early design version of the Boeing 747, a high wing transport with externally blown flaps, a simplified 3D high-lift wing, and a Boeing 777-200. Most impressive is their effort to reduce the time required to generate the surface and volume grids, to obtain the flow solution, and to post-process the data.…”

Section: Three-dimensional Methodsmentioning

confidence: 99%

See 1 more Smart Citation

The aerodynamic design of multi-element high-lift systems for transport airplanes

Dam¹

2002

Progress in Aerospace Sciences

254

109

View full text Add to dashboard Cite

High-lift systems have a major influence on the sizing, economics, and safety of most transport airplane configurations. The combination of complexity in flow physics, geometry, and system support and actuation has historically led to a lengthy and experiment intensive development process. However, during the recent past engineering design has changed significantly as a result of rapid developments in computational hardware and software. In aerodynamic design, computational methods are slowly superseding empirical methods and design engineers are spending more and more time applying computational tools instead of conducting physical experiments to design and analyze aircraft including their high-lift systems. The purpose of this paper is to review recent developments in aerodynamic design and analysis methods for multi-element high-lift systems on transport airplanes. Attention is also paid to the associated mechanical and cost problems since a multi-element high-lift system must be as simple and economical as possible while meeting the required aerodynamic performance levels. r

show abstract

Section: Three-dimensional Methodsmentioning

confidence: 99%

“…31. Comparison of time required to obtain a RANS solution using structured overset grid methodology [68].…”

Section: Three-dimensional Methodsmentioning

confidence: 99%

The aerodynamic design of multi-element high-lift systems for transport airplanes

Dam¹

2002

Progress in Aerospace Sciences

254

109

View full text Add to dashboard Cite

show abstract

“…27 ). The Chimera technique has often been applied in the CFD study of high-lift devices (Rogers et al 28 , Liao, Cai and Tsai 29 , Levesque, Pigeon and Deloze 30 ) and, more recently, for windturbine simulations (Santo et al. 25 , Yu and Kwon 31 , Sayed et al 32 ).…”

Section: Several Models and Simulation Methodologies Aimed At Modellimentioning

confidence: 99%

Three-dimensional fluid-structure interaction simulations of a yarn subjected to the main nozzle flow of an air-jet weaving loom using a Chimera technique

Delcour

Peeters

Degroote

2019

Textile Research Journal

View full text Add to dashboard Cite

In air-jet weaving looms, the main nozzle pulls the yarn from the prewinder by means of a high velocity air flow. The flexible yarn is excited by the flow and exhibits high amplitude oscillations. The motion of the yarn is important for the reliability and the attainable speed of the insertion. Fluid-structure interaction simulations calculate the interaction between the air flow and the yarn motion and could provide additional insight into yarn behavior. However, the use of an arbitrary Lagrangian–Eulerian approach for the deforming fluid domain around a flexible yarn typically results in severe mesh degradation, vastly reducing the accuracy of the calculations or limiting the physical time that can be simulated. In this research, the feasibility of using a Chimera technique to simulate the motion of a yarn interacting with the air flow from a main nozzle was investigated. This methodology combines a fixed background grid with a moving component grid deforming along with the yarn. The component grid is, however, not constrained by the boundaries of the flow domain allowing for large deformations with limited mesh degradation. Two separate cases were investigated. In the first case, the yarn was considered to be clamped at the main nozzle inlet. For the second case, the yarn was allowed to move axially as the main nozzle pulled it from a drum storage system.

show abstract

“…The axisymmetric main component grids (core and boosters) were created first, followed by grids for all the protuberances that reside on the main components. Utilizing macros from the Chimera Grid Tools (CGT) [13,14] version 2.1p+ script library, scripts were created for all pre-processing steps needed prior to running the flow solver. These include the generation of surface and volume grids, creation of hole-cutting instructions for overset domain connectivity, prescription of boundary conditions in the flow solver input file, and specifications of components for forces and moments integration.…”

Section: Grid Generationmentioning

confidence: 99%

CFD Simulations of the Space Launch System Ascent Aerodynamics and Booster Separation

Rogers

Dalle²,

Chan

2015

53rd AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

This paper presents details of Computational Fluid Dynamic modeling of the Space Launch System during ascent. The primary focus of the paper is the flow simulation of the vehicle during ascent using the Overflow Navier-Stokes code. Computations of 739 first-stage flight conditions covering a range of Mach numbers, angles of attack, and roll angles were computed. The overset grid system contained 375 million grid points, and over 28 million CPU hours were used in the simulations. The simulations were run on the Pleiades supercomputer at the NASA Advanced Supercomputer Center at Ames Research Center. The data products from this work include integrated line-loads, surface pressure coefficients, venting pressures, and protuberance air-loads. Detailed comparisons were made of the aerodynamic performance predicted by Overflow and the wind-tunnel derived aerodynamic database. A small number of the cases were run with two different turbulence models and with two differencing schemes. These results were used to quantify the sensitivity to the choice of the turbulence model and to the differencing scheme. The paper also introduces an effort to use the inviscid, unstructured Cartesian solver Cart3D to compute the aerodynamics during booster separation. Adaptive mesh refinement is being used to enable accurate simulations of sixteen booster-separation-motor plumes. The use of this tool is explored in preparation for building a booster-separation aerodynamic database.

show abstract

Advances in overset CFD processes applied to subsonic high-lift aircraft

Cited by 44 publications

References 21 publications

The aerodynamic design of multi-element high-lift systems for transport airplanes

The aerodynamic design of multi-element high-lift systems for transport airplanes

Three-dimensional fluid-structure interaction simulations of a yarn subjected to the main nozzle flow of an air-jet weaving loom using a Chimera technique

CFD Simulations of the Space Launch System Ascent Aerodynamics and Booster Separation

Contact Info

Product

Resources

About