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Aerospace Computational Design Laboratory: Technical Reports

Research and Teaching Output of the MIT Community

Aerospace Computational Design Laboratory: Technical Reports

 

Recent Submissions

  • 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 ...
  • 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 ...
  • 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)
  • 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 ...
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