Aerothermodynamic Design Optimization of Hypersonic Vehicles

Aerothermodynamic Design Optimization of Hypersonic Vehicles Eyi, Sinan; Boyd, Iain D. (American Institute of Aeronautics and Astronautics (AIAA), 2019-04-01) The objective of this study is to develop a reliable and efficient design optimization method for hypersonic vehicles focused on aerothermodynamic environments. Considering the nature of hypersonic flight, a high-fidelity aerothermodynamic analysis code is used for the simulation of weakly ionized hypersonic flows in thermochemical nonequilibrium. A gradient-based method is implemented for optimization. Bezier or nonuniform rational basis spline curves are used to parametrize the geometry or the geometry ch...
Aerothermodynamic design optimization in hypersonic flows Eyi, Sinan (2013-01-01) © 2013, American Institute of Aeronautics and Astronautics Inc. All rights reserved.The objective of this study is to develop a reliable and efficient design tool that can be used in hypersonic flows. The flow analysis is based on the axisymmetric Euler and the finite rate chemical reaction equations. These coupled equations are solved by using Newton’s method. The analytical and numerical methods are used to calculate Jacobian matrices. The effects of error in numerical Jacobians on the performance of flow...
Aerothermodynamic design optimization in hypersonic flows Eyi, Sinan (2013-09-16) The objective of this study is to develop a reliable and efficient design tool that can be used in hypersonic flows. The flow analysis is based on the axisymmetric Euler and the finite rate chemical reaction equations. These coupled equations are solved by using Newton's method. The analytical and numerical methods are used to calculate Jacobian matrices. The effects of error in numerical Jacobians on the performance of flow and sensitivity analyses are studied. A gradient based numerical optimization is us...
Aerothermodynamic shape optimization of hypersonic blunt bodies Eyi, Sinan (2015-07-03) The aim of this study is to develop a reliable and efficient design tool that can be used in hypersonic flows. The flow analysis is based on the axisymmetric Euler/Navier-Stokes and finite-rate chemical reaction equations. The equations are coupled simultaneously and solved implicitly using Newton's method. The Jacobian matrix is evaluated analytically. A gradient-based numerical optimization is used. The adjoint method is utilized for sensitivity calculations. The objective of the design is to generate a h...
Aerothermodynamic modeling and simulation of gas turbines for transient operating conditions Koçer, Gülru; Uzol, Oğuz; Department of Aerospace Engineering (2008) In this thesis, development of a generic transient aero-thermal gas turbine model is presented. A simulation code, gtSIM is developed based on an algorithm which is composed of a set of differential equations and a set of non-linear algebraic equations representing each gas turbine engine component. These equations are the governing equations which represents the aero-thermodynamic process of the each engine component and they are solved according to a specific solving sequence which is defined in the simul...

Citation Formats

S. Eyi and I. D. Boyd, “Aerothermodynamic Design Optimization of Hypersonic Vehicles,” 2018, vol. 2018, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/39122.