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Browsing Aerospace Computational Design Laboratory by Title

Bayt, Robert L.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199906)
Various trends in the spacecraft industry are driving the development of lowthrust propulsion systems. These may be needed for fine attitude control, or to reduce the mass of the propulsion system through the use of small ...

Oliver, Todd A.; Darmofal, David L.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200609)
The effects of dual consistency on discontinuous Galerkin (DG) discretizations of solution
and solution gradient dependent source terms are examined. Two common discretizations are
analyzed: the standard weighting technique ...

Venditti, David A.; Darmofal, David L.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200708)
Anisotropic grid–adaptive strategies are presented for viscous flow simulations in which the accurate prediction of multiple aerodynamic outputs (such as the lift, drag, and moment coefficients) is required from a single ...

Willcox, Karen; Peraire, Jaime; White, Jacob
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1999)
A linear reducedorder aerodynamic model is developed for aeroelastic analysis of turbomachines. The basis vectors are constructed using a block Arnoldi method. Although the model is cast in the time domain in statespace ...

Lindquist, Dana Rae
(Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 198805)

SauerBudge, A. M.; Bonet, J.; Huerta, A.; Peraire, J.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 2003)
We present a method for Poisson’s equation that computes guaranteed upper and lower bounds for the values of linear functional outputs of the exact weak solution of the infinite dimensional continuum problem using traditional ...

Stirling, Leia Abigail
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200806)
Past spaceflight missions have shown that astronauts adapt their motorcontrol strategies to the microgravity environment. Even though astronauts undergo hundreds of training hours, the strategies for locomotion and ...

Duffner, John D.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200806)
Gas turbine vanes have airfoil shapes optimized to deliver specific flow conditions to turbine rotors. The limitations of the manufacturing process with regards to accuracy and precision mean that no vane will exactly match ...

Wong, J. S.; Darmofal, D. L.; Peraire, J.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200104)
We present a high order accurate streamlineupwind/PetrovGalerkin (SUPG) algorithm for the solution of the compressible Euler and NavierStokes equations. The flow equations are written in terms of entropy variables which ...

Mughal, Bilal Hafeez
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199802)
Several distinct issues important in integral approximations of the threedimensional boundarylayer equations are addressed. One of these is the requirement, justified on the basis of the nature of the full differential ...

Vermeersch, Sabine
(Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199210)
The investigation of the vortical flow around the F117A Stealth Fighter is presented in
order to demonstrate the capability to resolve leading edge vortices with an adaptive
finite element solver for the Euler equations. ...

Yano, Masayuki
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200906)
A highorder Galerkin LeastSquares (GLS) finite element discretization is combined
with massively parallel implicit solvers. The stabilization parameter of the GLS
discretization is modified to improve the resolution ...

Arkilic, Errol B.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199701)
An analytic and experimental investigation into gaseous
flow with slight rarefaction through long microchannels
is undertaken in an attempt to obtain values of the Tangential Momentum Accommodation Coefficient
(TMAC) ...

Tan, BuiThanh
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200705)
Most model reduction techniques employ a projection framework that utilizes a reducedspace basis. The basis is usually formed as the span of a set of solutions of the largescale system, which are computed for selected ...

Wogrin, Sonja
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200806)
In many settings, distributed sensors provide dynamic measurements over a specified time horizon that can be used to reconstruct information such as parameters, states or initial conditions. This estimation task can be ...

BuiThanh, T.; Willcox, K.; Ghattas, O.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200708)
A modelconstrained adaptive sampling methodology is proposed for reduction of largescale systems with highdimensional parametric input spaces. Our model reduction method uses a reduced basis approach, which requires the ...

Lee, Kuok Ming
(Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 198910)
Euler and NavierStokes results are presented for a blunt delta wing at Mach
7.15 and 300 angle of attack. The viscous calculations were done at a Reynolds
number based on chord of 5.85 x 106 with freestream and wall ...

Yano, Masayuki; Darmofal, David L.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 20110921)
This report analyzes the behavior of three variants of the dualweighted residual (DWR) error estimates applied to the pdependent discretization that results from the BR2 discretization of a secondorder PDE. Three error ...

Fidkowski, Krzysztof J.; Darmofal, David L.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 200610)
This report presents a mesh adaptation method for higherorder (p > 1) discontinuous Galerkin (DG) discretizations of the twodimensional, compressible NavierStokes equations. The method uses a mesh of triangular elements ...

Vailong, Hubert J. B.
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199702)
One of the major difficulties faced in the numerical resolution of the equations of physics is to decide on the right balance between computational cost and solutions accuracy, and to determine how solutions errors affect ...