Engineering topics
Housman, Jeffrey
Publications and source records attributed to Housman, Jeffrey.
Jet Noise Prediction for Low Boom Aircraft
Enabling jet acoustics simulations on full scale flight vehicles utilizing zonal hybrid RANS/LES within the Launch Ascent and Vehicle Aerodynamics (LAVA) Solver. Hybrid RANS/LES technology will assist in the development for innovative concepts for integrated supersonic propulsion systems. Modeling and simulation practices must be scrutinized further and new methods need to be developed.
Launch, Ascent, and Vehicle Aerodynamics Scale-Resolving Simulations for NASA Applications
No abstract available
High-Resolution Launch Environment Simulations
After many years of harsh rocket launches, the Main Flame Deflector (MFD) at Kennedy Space Center has been upgraded in anticipation of flights of NASA’s next generation Space Launch System. The new MFD has a much easier to maintain shingled steel surface.
Wall Modeled Lattice Boltzmann and Navier-Stokes Approaches for Selected RCA Cases
No abstract available
Jet Noise Prediction Using Hybrid RANS/LES with Structured Overset Grids
No abstract available
Jet Noise Prediction Using Hybrid RANS/LES with Structured Overset Grids
No abstract available
Category 7: Slat Cove Noise A Zonal Hybrid RANS/LES Approach to Slat Noise Simulation
No abstract available
Computational Studies for Sonic Boom Prediction
Outline: Introduction; Launch Ascent and Vehicle Aerodynamics (LAVA) Framework; 1st AIAA Sonic Boom Prediction Workshop Oblique Shock/Plume Interaction; Summary.
High Fidelity Simulations for Unsteady Flow Through the Orbiter LH2 Feedline Flowliner
High fidelity computations were carried out to analyze the orbiter M2 feedline flowliner. Various computational models were used to characterize the unsteady flow features in the turbopump, including the orbiter Low-Pressure-Fuel-Turbopump (LPFTP) inducer, the orbiter manifold and a test article used to represent the manifold. Unsteady flow originating from the orbiter LPFTP inducer is one of the major contributors to the high frequency cyclic loading that results in high cycle fatigue damage to the gimbal flowliners just upstream of the LPFTP. The flow fields for the orbiter manifold and representative test article are computed and analyzed for similarities and differences. An incompressible Navier-Stokes flow solver INS3D, based on the artificial compressibility method, was used to compute the flow of liquid hydrogen in each test article.
Comparison of Artificial Compressibility Methods
Various artificial compressibility methods for calculating the three-dimensional incompressible Navier-Stokes equations are compared. Each method is described and numerical solutions to test problems are conducted. A comparison based on convergence behavior, accuracy, and robustness is given.
Comparison of Artificial Compressibility Methods
Various artificial compressibility methods for calculating three-dimensional, steady and unsteady, laminar and turbulent, incompressible Navier-Stokes equations are compared in this work. Each method is described in detail along with appropriate physical and numerical boundary conditions. Analysis of well-posedness and numerical solutions to test problems for each method are provided. A comparison based on convergence behavior, accuracy, stability and robustness is used to establish the relative positive and negative characteristics of each method.