3 edition of **Grid sensitivity for aerodynamic optimization and flow analysis** found in the catalog.

Grid sensitivity for aerodynamic optimization and flow analysis

- 42 Want to read
- 5 Currently reading

Published
**1993**
by Old Dominion University Research Foundation, Dept. of Mechanical Engineering and Mechanics, College of Engineering and Technology, Old Dominion University, National Technical Information Service, distributor in Norfolk, Va, [Springfield, Va
.

Written in

- Fluid dynamics.,
- Aerodynamics.

**Edition Notes**

Statement | I. Sadrehaghighi and S.N. Tiwari. |

Series | [NASA contractor report] -- NASA CR-192980., NASA contractor report -- NASA CR-192980. |

Contributions | Tiwari, S. N., United States. National Aeronautics and Space Administration. |

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

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL14694454M |

Full text of "Simultaneous Aerodynamic and Structural Design Optimization (SASDO) for a 3-D Wing" See other formats AIAA Simultaneous Aerodynamic and Structural Design Optimization (SASDO) for a 3-D Wing Clyde R. Gumbert NASA Langley Research Center Hampton, Virginia Gene J.-W. Hou Old Dominion University Norfolk, Virginia Perry A. Newman NASA Langley Research Center . Aerodynamic shape optimization via discrete adjoint formulation using Euler equations on unstructured grids Grid Sensitivity Analysis 26 fi]. Aerodynamic design optimization via sensitivity analysis has been an important area of research in recent years. Currently used methods in aerodynamics .

Airfoil geometric uncertainty can generate aerodynamic characteristics fluctuations. Uncertainty quantification is applied to compute its impact on the aerodynamic characteristics. In addition, the contribution of each uncertainty variable to aerodynamic characteristics should be computed by the uncertainty sensitivity analysis. In the paper, Sobol&#x;s analysis is used for uncertainty. A methodology for aerodynamic shape optimization on two-dimensional unstructured grids using Euler equations is presented. The sensitivity derivatives are obtained using the discrete adjoint formulation. The Euler equations are solved using a fully implicit, upwind, cell-vertex, median-dual finite volume scheme. Roe's upwind flux-difference-splitting scheme is used to determine the inviscid.

A detailed and concise overview of sensitivity analysis methods and aerodynamic design optimization research may be found in Newman et al. ( Hino () used the Navier-Stokes equations coupled with a sequential quadratic programming (SQP) method to . The fixed Cartesian grid is employed within an Immersed Boundary body non-conformal solver and the alternating grid is used by body conformal solver. Category Science & Technology.

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Get this from a library. Grid sensitivity for aerodynamic optimization and flow analysis. [I Sadrehaghighi; S N Tiwari; United States. National Aeronautics and Space Administration.]. Grid sensitivity for aerodynamic optimization and flow analysis.

By I. Sadrehaghighi and S. Tiwari. Abstract. After reviewing relevant literature, it is apparent that one aspect of aerodynamic sensitivity analysis, namely grid sensitivity, has not been investigated extensively.

The grid sensitivity algorithms in most of these studies are Author: I. Sadrehaghighi and S. Tiwari. AIREX: Grid sensitivity for aerodynamic optimization and flow analysis After reviewing relevant literature, it is apparent that one aspect of aerodynamic sensitivity analysis, namely grid sensitivity, has not been investigated extensively.

The grid sensitivity algorithms in most of these studies are based on structural design models. Trove: Find and get Australian resources.

Books, images, historic newspapers, maps, archives and more.English, Article, Report, Government publication, Microform edition: Grid sensitivity for aerodynamic optimization and flow analysis [microform] / I. Sadrehaghighi and S.N. Tiwari Grid sensitivity for aerodynamic optimization and.

The accuracy of aerodynamic shape sensitivity derivatives is validated on two viscous test problems: internal flow through a double-throat nozzle and external flow over a NACA 4-digit airfoil.

Grid sensitivity and aerodynamic optimization of generic airfoils. A discrete semi-analytical procedure for aerodynamic sensitivity analysis including grid sensitivity.

Three-dimensional aerodynamic shape sensitivity analysis and design optimization using the Euler equations on unstructured grids.

sensitivity analysis and optimization of coupled thermal and flow problems with applications to contraction design International Journal for Numerical Methods in Fluids, Vol. 23, No. 10 Rapid design space approximation for two-dimensional transonic aerofoil design.

Grid Discretization Study for the Efficient Aerodynamic Analysis of the Very Light Aircraft (VLA) Configuration Moses Sitio*, Sangho Kim**and Jaewoo Lee*** Department of Aerospace Information Engineering, Konkuk University,Seoul, Republic of Korea Abstract.

The analytic evaluation of sensitivity derivatives requires an additional level of simulation referred to as sensitivity analysis. For aerodynamic optimization, the state equation is a system of nonlinear partial differential equations (PDE) expressing the conservation of mass, momentum, and energy.

Grid Sensitivity Issue If you are writing a thesis for your master or PhD relating to the use of a CFD code to an engineering application or to any other application then it is required from you to conduct a grid sensitivity test, the following document provides the required guidelines by the Journal of Fluids Engineering Editorial Policy Statement on the Control of Numerical Accuracy.

A three-dimensional unstructured grid approach to aerodynamic shape sensitivity analysis and design optimization has been developed and is extended to model geometrically complex configurations. The advantage of unstructured grids (when compared with a structured-grid approach) is their inherent ability to discretize irregularly shaped.

The calculation of the derivatives of output quantities of aerodynamic flow codes, commonly known as numerical sensitivity analysis, has recently become of increased importance for a variety of applications in flow analysis, but the original motivation came from the field of aerodynamic shape optimization.

Various pre-and post-processing techniques for overset flow analysis and sensitivity analysis are devised or implemented to adapt overset mesh technique to the design optimization problem based on.

Sensitivity Analysis Direct Differentiation Method The discrete residual vector of nonlinear aerodynamic analysis for steady problems can be written symbolically as R[Q(β),X(β),β]=0, (3) where X is the grid position vector, and b is the vector of design variables.

Boundary conditions are. An automated aerodynamic design optimization strategy is outlined which includes the use of a design optimization program, an aerodynamic flow analysis code, an aerodynamic sensitivity and approximate analysis code, and a mesh regeneration and grid sensitivity analysis code.

The elliptic grid sensitivity analysis has been performed on a two-dimensional elliptic grid whereas the hyperbolic grid sensitivity analysis has been performed for a three-dimensional hyperbolic grid. computational domain. Based on this observation, overlap optimization is extended to sensitivity analysis module to improve the convergence and accuracy characteristics.

Spline-Boundary intersecting Grid (S-BIG) Scheme To calculate the aerodynamic coefficients in overset flow analysis, the zipper grid scheme is widely used.[5]. An efficient aerodynamic shape optimization method based on a computational fluid dynamics/sensitivity analysis algorithm has been developed which determines automatically the geometrical definition of an optimal surface starting from any initial arbitrary geometry.

CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): An algorithm is developed to obtain the grid sensitivity with respect to design parameters for aerodynamic optimization.

The procedure is advocating a novel (geometrical) parameterization using spline functions such as NURBS (Non-Uniform Rational BSplines) for defining the airfoil geometry. In the pre-processing, the convergence characteristics of the flow solver and sensitivity analysis are improved by overlap optimization method.

Moreover, a new post-processing method, Spline-Boundary Intersecting Grid (S-BIG) scheme, is proposed by considering the ratio of cell area for more refined prediction of aerodynamic coefficients and.

In aerodynamic shape optimization, gradient-based methods often rely on the adjoint approach, which is capable of computing the objective function sensitivities with respect to the design variables. In the literature adjoint approaches are proved to outperform other relevant methods, such as the direct sensitivity analysis, finite differences.– Time-dependent aerodynamics (2D) – Time-dependent coupled aero-elastic (3D) • Focus – Adjoint formulation • Hand coded (occasional use of AD) • Same data structures/solution techniques as analysis • Verification – Exact full sensitivities in all cases – Optimization examples are .Grid sensitivity analysis for the calibration of a prognostic meteorological model in complex terrain by a screening experiment [An article from: Environmental Modelling and Software] [Zoras, S., Triantafyllou, A.G., Hurley, P.J.] on *FREE* shipping on qualifying offers.

Grid sensitivity analysis for the calibration of a prognostic meteorological model in complex terrain by a Author: S. Zoras, A.G. Triantafyllou, P.J. Hurley.