by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English
|Statement||submitted by Chuen-Yen Chow; principal investigator.|
|Series||NASA contractor report -- NASA CR-193616.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Analysis of the Harrier forebody/inlet design using computational techniques. computations of transonic flow past the complex forebody/inlet configuration of the AV-8B Harrier II have been performed. The actual aircraft configuration was measured and its surface and surrounding domain were defined using computational structured grids Author: Chuen-Yen Chow. Analysis of the Harrier forebody/inlet design using computational techniques computations of transonic flow past the complex forebody/inlet configuration of the AV-8B Harrier II have been. Analysis of the Harrier forebody/inlet design using computational techniques and surrounding domain were defined using computational structured grids. the simplifications incorporated into. Javaid and Serghides [44,45], used the cone-derived waverider as the first-stage precompression surface to design the forebody/inlet integration vehicle, .
Mixed-compression hypersonic inlet for the combined cycle engine is designed based on aerodynamic theory and Oswatitsch best shock wave theory. Its performances are obtained using CFD (Computational Fluid Dynamics) technology. Firstly, an aircraft flight trajectory is selected with its cruise condition fixed as inlet design point. An Introduction to Computational Fluid Mechanics by Example(1st Edition) by Sedat Biringen, Chuen-Yen Chow Printed Access Code, Pages, Published by John Wiley & Sons ISBN , ISBN: In this paper, a computational tool called Turbine Engine Analysis Compressor Code (TEACC) is used to evaluate the effect of inlet distortion on a three-stage military fan. This three-stage military fan is further connected to an F inlet and forebody operating at an angle of attack and sideslip to demonstrate the effect of inlet distortion. A CFD (Computational Fluid Dynamics) model was developed to simulate flow in a membrane oxygenator. i.e. forebody/inlet, combustor and afterbody/nozzle. Analysis and design procedures of.
Computational analysis of co- and contra-rotating streamwise vortices in a turbulent boundary layer. Navier-Stokes simulation of external/internal transonic flow on the forebody/inlet of the AV-8B Harrier II. STEPHEN MYSKO, WEI CHYU, Practical Design and Optimization in Computational Fluid Dynamics. W. Huffman, R. Melvin, D. Young, F. Book May with Reads Phase I, the forebody-inlet-isolator design and analysis, phase II, the combustor-diffuser-nozzle design and analysis and phase III, . The CFD-based investigation was conducted on a 2-D wind-tunnel model geometry of a forebody and inlet at a freestream Mach number of 5. A sequence of steady-state solutions were run to map the inlet flowfield response to subsequent increases in back-pressure from a design value up to the point of imminent unstart. Materials Design Using Computational Intelligence Techniques book. By Shubhabrata Datta. Edition 1st Edition. First Published eBook Published 26 October These approaches are getting more attention with the application of computational intelligence techniques. This book illustrates the alternative but effective methods of designing.