Now showing items 1-20 of 33

    • A Comparison of Numerical Schemes on Triangular and Quadrilateral Models 

      Lindquist, Dana Rae (Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1988-05)
    • A Semi-Implicit Navier-Stokes Solver and Its Application to a Study of Separated Flow about Blunt Delta Wings 

      Loyd, Bernard (Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1989-02)
      A novel semi-implicit scheme for the Navier-Stokes equations is presented and evaluated. The semi-implicit scheme combines an implicit temporal integration in the bodynormal directions with explicit temporal integrations ...
    • Visualization of Three Dimensional CFD Results 

      Unknown author (Computational Fluid Dynamics Laboratory, 1989-05-01)
      We have developed an interactive graphics system for the display of three dimensional CFD solutions on unstructured hexahedral grids. This system is implemented on a high-performance graphics supercomputer. Visualization ...
    • Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing 

      Lee, Kuok Ming (Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1989-10)
      Euler and Navier-Stokes 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 ...
    • Investigation of the F117A Vortical Flow Characteristics Preliminary Results 

      Vermeersch, Sabine (Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1992-10)
      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. ...
    • Adaptive Mesh Euler Equation Computations of Vortex Breakdown in Delta Wing Flow 

      Modiano, David (Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1993-01)
      A solution method for the three-dimensional Euler equations is formulated and implemented. The solver uses an unstructured mesh of tetrahedral cells and performs adaptive refinement by mesh-point embedding to increase ...
    • Small-Scale Forcing of a Turbulent Boundary Layer 

      Lorkowski, Thomas (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-01)
      In order to understand the effect of small scale forcing on turbulent flows and its implications on control, an experimental investigation is made into the forcing of the inertial scales in the wall region of a turbulent ...
    • Measurement of the Mass Flow and Tangential Momentum Accommodation Coefficient in Silicon Micromachined Channels 

      Arkilic, Errol B. (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-01)
      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) ...
    • Silicon micromachined sensors and sensor arrays for shear-stress measurements in aerodynamic flows 

      Padmanabhan, Aravind (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-02)
      In this thesis we report on a new micromachined floating-element shear-stress sensor for turbulent boundary layer research. Applications in low shear-stress environments such as turbulent boundary layers require extremely ...
    • Analysis and design of axisymmetric transonic flow with linearized three-dimensional flow prediction 

      Ahn, Jon (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-02)
      The primary goal of this thesis is the application of the proven stream-surface based Newton method to analysis/design of an axisymmetric nacelle with the actuator disk modeling of a fan. And to further utilize the benefits ...
    • A Posteriori Bounds for Linear Functional Outputs of Hyperbolic Partial Differential Equations 

      Vailong, Hubert J. B. (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-02)
      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 ...
    • System Identification and Active Control of a Turbulent Boundary Layer 

      Rathnasingham, Ruben (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-06)
      An experimental investigation is made into the active control of the near-wall region of a turbulent boundary layer using a linear control scheme. System identification in the boundary layer provides optimal transfer ...
    • System Identification and Active Control of a Turbulent Boundary Layer 

      Rathnasingham, Ruben (Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1997-06)
      An experimental investigation is made into the active control of the near-wall region of a turbulent boundary layer using a linear control scheme. System identification in the boundary layer provides optimal transfer ...
    • Integral methods for three-dimensional boundary layers 

      Mughal, Bilal Hafeez (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1998-02)
      Several distinct issues important in integral approximations of the three-dimensional boundary-layer equations are addressed. One of these is the requirement, justified on the basis of the nature of the full differential ...
    • Aerodynamic Optimization Based on the Euler and Navier-Stokes Equations using Unstructured Grids 

      Elliott, Jonathan Kindred (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1998-06)
      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 ...
    • An Arnoldi Approach for Generation of Reduced Order Models for Turbomachinery 

      Willcox, Karen; Peraire, Jaime; White, Jacob (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1999)
      A linear reduced-order aerodynamic model is developed for aeroelastic analysis of turbo-machines. The basis vectors are constructed using a block Arnoldi method. Although the model is cast in the time domain in state-space ...
    • Analysis, Fabrication and Testing of a MEMS-based Micropropulsion System 

      Bayt, Robert L. (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1999-06)
      Various trends in the spacecraft industry are driving the development of low-thrust propulsion systems. These may be needed for fine attitude control, or to reduce the mass of the propulsion system through the use of small ...
    • Reduced-order aerodynamic models for aeroelastic control of turbomachines 

      Willcox, Karen Elizabeth (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 2000-02)
      Aeroelasticity is a critical consideration in the design of gas turbine engines, both for stability and forced response. Current aeroelastic models cannot provide high-fidelity aerodynamics in a form suitable for design ...
    • High Order Finite Element Discretization of the Compressible Euler and Navier-Stokes Equations 

      Wong, J. S.; Darmofal, D. L.; Peraire, J. (Aerospace Computational Design Laboratory, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 2001-04)
      We present a high order accurate streamline-upwind/Petrov-Galerkin (SUPG) algorithm for the solution of the compressible Euler and Navier-Stokes equations. The flow equations are written in terms of entropy variables which ...
    • Computing Bounds for Linear Functionals of Exact Weak Solutions to Poisson’s Equation 

      Sauer-Budge, 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 ...