3 edition of **Unstructured and adaptive mesh algorithms for aerodynamic calculations** found in the catalog.

Unstructured and adaptive mesh algorithms for aerodynamic calculations

- 29 Want to read
- 3 Currently reading

Published
**1992**
by Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va
.

Written in English

- Aerodynamics.,
- Numerical grid generation (Numerical analysis)

**Edition Notes**

Statement | D.J. Mavriplis. |

Series | NASA contractor report -- 189685., ICASE report -- no. 91-35., NASA contractor report -- NASA CR-189685., ICASE report -- no. 91-35. |

Contributions | Institute for Computer Applications in Science and Engineering. |

The Physical Object | |
---|---|

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL14686483M |

An automated method for grid independence is developed for two-dimensional unstructured wall function grids. Grid independence is achieved via successive levels of adaptive refinement. Adaptive refinement is performed in an automated manner Cited by: 2. aerodynamic applications in the field of aeronautics and astronautics. HUNS3D flow solver [6], [7] designed for both 2D and 3D CFD simulations, is a finite volume unstructured. Aerodynamic and Static Aeroelastic Analysis of a Transonic Wing using Hybrid Unstructured Flow Solver.

MESH GENERATION FOR THE COMPUTATION OF FLOW'FIELDS OVER COMPLEX AERODYNAMIC SHAPES TIMOTHY BAKER Departmen~ of Mer]~ardcal and Aerospace Engineering En~neerlng Quadrangle, Princeton Unlverslty, Princeton, NJ , U.S.A. AbstractmMethods are presented for generating both structured and unstructured meshes about. The AIRPLANE15,16 volume mesh of tetrahedra is de-formed rather than regenerated using MESHMV. This code also preserves the number of points and connec-tivity of the original mesh. If the method should invert any tetrahedra, the entire mesh is automatically regen-erated using MESH3D Following this, the multigrid version of AIRPLANE is run.

a large design space, Adaptive Range GA (ARGA) was proposed by Arakawa and Hagiwara for binary genetic algorithms [12]. AERODYNAMIC SHAPE OPTIMIZATION WITH A NEW PARALLEL EVOLUTIONARY ALGORITHM AND NUMERICAL FLOW MODELLING A. Jahangirian, M. Ebrahimi Aerospace Engineering Department, Amirkabir University of . With an unstructured mesh flow solver, and an automatic triangulation capability, it is possible to contemplate the solution of transient flows using these adaptive grid methods. The combined procedures were applied to simulate the blast wave produced by an exploding vessel (Morgan et al. a, b).Cited by:

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Unstructured and adaptive mesh algorithms for aerodynamic calculations (SuDoc NAS ) [Dimitri Mavriplis] on *FREE* shipping on qualifying offers.

Get this from a library. Unstructured and adaptive mesh algorithms for aerodynamic calculations. [Dimitri Mavriplis; Institute for Computer Applications in Science and Engineering.]. Mavriplis D.J.

() Unstructured mesh algorithms for aerodynamic calculations. In: Napolitano M., Sabetta F. (eds) Thirteenth International Conference on Numerical Methods in Fluid Dynamics. Lecture Notes in Unstructured and adaptive mesh algorithms for aerodynamic calculations book, vol Cited by: A scalability result and performance on SGI Origin are shown in Fig.

Figure 6(a) indicates a super-linear speedup. This super-linear speedup is due to the L2 cache hit rate as shown in Fig. 6(b) where the MFLOPS values per processor increases along with a L2 cache hit rate.

Super scalability occasionally occurs in cache-based architecture system. @article{osti_, title = {Extreme scale unstructured adaptive CFD for aerodynamic flow control}, author = {Jansen, Kenneth E. and Rasquin, Michel and Brown, Jed and Smith, Cameron and Shephard, Mark S.

and Carothers, Chris}, abstractNote = {Understanding the flow of fluid, either liquid or gas, through and around solid bodies has challenged man since the dawn of. Unstructured adaptive mesh calculations for NASA TRAP WING using the code HiFUN Ravindra K., Nikhil Vijay Shende, Sumit Kumar Patel & N.

Balakrishnan CAd Lab, Department of Aerospace Engg., IISc, Bangalore 30th AIAA Applied Aerodynamics Conference, New Orleans, LA June These proceedings of a well-established conference on numerical methods, calculations, and modelling in fluid dynamics concentrates on five topics: multidimensional upwinding, turbulent flows, domain decomposition methods, unstructured grids, and flow visualization, and it includes papers presented at a workshop on all-vertex schemes.

Email your librarian or administrator to recommend adding this book to your organisation's collection. Applied Computational Aerodynamics “Unstructured Mesh Algorithms for Aerodynamic Calculations,” ICASE Report No. (also NASA Pirzadeh, S., “Vortical Flow Prediction Using an Adaptive Unstructured Grid Method,” Symposium on.

Thirteenth International Conference on Numerical Methods in Fluid Dynamics Unstructured mesh algorithms for aerodynamic calculations. Pages Performance assessment of an adaptive mesh refinement technique for detonation waves.

Pages Valorani, M. (et al.). with the unstructured mesh. We investigate how to improve the boundary layer resolution by using unstructured mesh near the object surface.

The unstructured mesh method is a computation method that is suitable for complex shapes because the unstructured mesh has high mesh arrangement flexibility. Therefore, it is a calculation method suitableFile Size: 1MB.

Aerodynamic shape optimization using efficient evolutionary algorithms and unstructured CFD solver. Another essential problem with GA is the massive calculations required for fitness evaluation by CFD flow solver until the convergence is reached.

Jahangirian A, Johnston LJ. Automatic generation of adaptive unstructured grid for viscous Cited by: An unstructured mesh Navier-Stokes computational fluid dynamics solver NSU3D is evaluated for wind turbine aerodynamic predictions and comparisons are made with the NREL Phase VI.

N-body algorithms on unstructured meshes Gravitational accelerations in N-body systems can be calculated either from particle-particle methods or particle-mesh techniques.

Below we introduce a new particle-mesh algorithm for unstructured grids. The discretized Poisson’s equation on an unstructured mesh can be derived as follows. Aerodynamic Design Optimization on Unstructured Meshes Using the Navier-Stokes Equations lems made use of finite-difference calculations to obtain sensitiv- ity information.

This technique can be used to obtain the the mesh vertices. Inviscid fluxes at cell interfaces are computedCited by: 2. Aerodynamic Design Optimization Problem Aerodynamic design optimization is simply a constrained minimization problem which attempts to reduce an objective or cost function F(Q, X, _k) subject to constraints Cj(Q,X,_k).

Here, Q is the aerodynamic state vector, X is the computational mesh, and _k is the vector. Adaptive refinement of the mesh interval (h) and the order of approximations (p) In the last few years methods using unstructured meshes have also begun to gain more general acceptance.

The Dassault-INRIA group led the way in developing a Essential Elements of Computational Algorithms for Aerodynamic. Evaluation of adaptive, unstructured CFD calculations of the flow around the DU91 airfoil. Evaluation of adaptive, unstructured CFD calcul ations of. main rotor, and other components, an overset mesh technique was adopted.

To enhance the spatial accuracy of the solution, a quasi-unsteady solution-adaptive mesh refinement technique was applied. For the application of the present method, calculations were made for the rotor-fuselage interaction of the ROBIN Size: KB. with complex geometries, the ability to easily incorporate adaptive mesh reﬁnement (AMR) strategies also became one of the often quoted advantages of the unstructured mesh approach,13,14,15,16,17,18 In the current day environment, unstructured mesh methods constitute one of the most prevalent approaches in computational Size: 5MB.

Aerodynamic design optimization on unstructured grids with a continuous adjoint formulation W. Kyle Anderson*, V. Venkatakrishnan NASA Langley Research Center, MSHampton, VAUSA Received 20 November ; accepted 18 May Abstract A continuous adjoint approach for obtaining sensitivity derivatives on unstructured grids is.

Unstructured Mesh Algorithms for Aerodynamic Calculations p. 57 Fluid Flow Visualization: Recent Developments and Future Directions p. 78 A Multi-Dimensional Solution Adaptive Multigrid Solver for the Euler Equations p.

90 A Multi-Dimensional Upwind Scheme for the Euler Equations p. 95 On a Method to Construct Godunov-Type Schemes p. Aerodynamic shape optimization via discrete adjoint formulation using Euler equations on unstructured grids by Bijoyendra N'alh A dissertation submitted to the graduate faculty in partial fulfillment of the requirements for the degree of DOCTOR OF PHILOSOPHY Major: Aerospace Engineering Major Professors: Richard G.

Hindman M. \'ogel.Unsteady Aerodynamic Design on Unstructured Meshes with Sliding Interfaces on⇤,FranciscoPalacios †, mesh algorithm for unstructured meshes is also developed and tested. The gradient infor- of computational resources and advanced algorithms, accurately predicting and designing for the per.