Browsing Aerospace Computational Design Laboratory by Title
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Adaptive Mesh Euler Equation Computations of Vortex Breakdown in Delta Wing Flow
(Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199301)A solution method for the threedimensional Euler equations is formulated and implemented. The solver uses an unstructured mesh of tetrahedral cells and performs adaptive refinement by meshpoint embedding to increase ... 
Aerodynamic Optimization Based on the Euler and NavierStokes Equations using Unstructured Grids
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199806)The overall problem area addressed is that of efficient aerodynamic shape design through the use of computational fluid dynamics (CFD). A method is presented for performing optimization including modal inverse design and ... 
Analysis and design of axisymmetric transonic flow with linearized threedimensional flow prediction
(Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 199702)The primary goal of this thesis is the application of the proven streamsurface based Newton method to analysis/design of an axisymmetric nacelle with the actuator disk modeling of a fan. And to further utilize the benefits ... 
Analysis of Dual Consistency for Discontinuous Galerkin Discretizations of Source Terms
(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 ... 
Analysis, Fabrication and Testing of a MEMSbased Micropropulsion System
(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 ... 
Anisotropic Grid Adaptation for Multiple Aerodynamic Outputs
(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 ... 
An Arnoldi Approach for Generation of Reduced Order Models for Turbomachinery
(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 ... 
A Comparison of Numerical Schemes on Triangular and Quadrilateral Models
(Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 198805) 
Computing Bounds for Linear Functionals of Exact Weak Solutions to Poisson’s Equation
(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 ... 
Development of Astronaut Reorientation Methods: A Computational and Experimental Study
(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 ... 
The effects of manufacturing variability on turbine vane performance
(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 ... 
High Order Finite Element Discretization of the Compressible Euler and NavierStokes Equations
(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 ... 
Integral methods for threedimensional boundary layers
(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 ... 
Investigation of the F117A Vortical Flow Characteristics Preliminary Results
(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. ... 
Massively Parallel Solver for the HighOrder Galerkin LeastSquares Method
(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 ... 
Measurement of the Mass Flow and Tangential Momentum Accommodation Coefficient in Silicon Micromachined Channels
(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) ... 
Model Reduction for Dynamic Sensor Steering: A Bayesian Approach to Inverse Problems
(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 ... 
Model Reduction for LargeScale Systems with High Dimensional Parametric Input Space
(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 ... 
ModelConstrained Optimization Methods for Reduction of Parameterized LargeScale Systems
(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 ... 
Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing
(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 ...