3 edition of Viscous three-dimensional analyses for nozzles for hypersonic propulsion found in the catalog.
Viscous three-dimensional analyses for nozzles for hypersonic propulsion
G. J. Harloff
by Sverdrup Technology, Inc., NASA Lewis Research Center Group, For sale by the National Technical Information Service in Cleveland, Ohio, [Springfield, Va
Written in English
|Other titles||Viscous three dimensional analyses for nozzles for hypersonic propulsion.|
|Statement||G.J. Harloff, D.R. Reddy and H.T. Lai.|
|Series||NASA contractor report -- 185197., NASA contractor report -- NASA CR-185197.|
|Contributions||Reddy, D. R., Lai, H. T., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Propulsion system performance, the gas generator Brayton cycle, zero dimensional analysis of ideal ramjet, turbojet and turbofan cycles, non-ideality and isentropic efficiencies. Performance analysis of inlets and nozzles, gas turbine combustors, compressors and turbines and discussion of . Abstract. Various papers on numerical methods for engine-airframe integration are presented. The individual topics considered include: scientific computing environment for the s, overview of prediction of complex turbulent flows, numerical solutions of the compressible Navier-Stokes equations, elements of computational engine/airframe integrations, computational requirements for efficient.
Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging. The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves. The detonation wave initiation in detonation tube in Cited by: The renewed interest in high-speed propulsion has led to increased activity in the development of the supersonic combustion ramjet engine for hypersonic flight applications. In the hypersonic regime the scramjet engine's specific thrust exceeds that of other propulsion systems. This book, written by a leading researcher, describes the processes.
multi-body aerodynamics. In high-speed propulsion systems, shock-boundary layer interaction (SBLI) can occur in intakes, supersonic combustion chambers and nozzles. Computational fluid dynamics (CFD) is routinely used to study SBLI flows and predict such interactions in geometries of practical interest. This volume - the third and final in a mini-series on hypersonic propulsion along with High Speed Flight Propulsion Systems, volume , and Developments in High Speed Flight Propulsion Systems, volume - presents a comprehensive and detailed exposition of the gradual maturing of scramjet technologies.
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VISCOUS THREE-DIMENSIONAL ANALYSES FOR NOZZLES FOR HYPERSONIC PROPULSION G.J. Harloff. 9.R. Reddy, and H.T. Lai Sverdrup Tec-hnology Inc. NASA Lewis Research Center Group Cleveland, Ohio SUMEIARY A Navier-Stokes computer code has been validated using a number of two- and three-dimensional configurations for both laminar and turbulent flows.
Get this from a library. Viscous three-dimensional analyses for nozzles for hypersonic propulsion. [G J Harloff; D R Reddy; H T Lai; United States. National Aeronautics and Space Administration.].
PERSPECTIVES ON HYPERSONIC VISCOUS AND NONEQUILIBRIUM FLOW RESEARCH H.K. Cheng Department of Aerospace Engineering University of Southern California Los Angeles CA FOREWORD This report (USCAE ) is based on a study prepared for the article "Perspectives on Hypersonic Viscous Flow Research" in the Annual Reviews of Fluid Mechanics.
Gary Harloff currently works at the Private Client Group, Harloff Capital Management, and manages money for high net worth individuals and manages a hedge fund.
Gary does research in Computational. The three-dimensional nozzles with shape transition are designed at a typical hypersonic flight condition and the entry parameters are identical to the work of Mo et al., as illustrated in Table 2.
The entry and exit shapes of the three-dimensional nozzles are shown in Fig. 7, and the entry and exit areas are and mm 2 Cited by: 3. Homogeneous gas flow in a viscous, hypersonic three-dimensional shock layer near the stagnation point was studied in /5/.
*,48,2, 1. Let us consider a three-dimensional hypersonic flow of gas containing spherical particles of radius a and density p,past a blunt : S.V. Peigin. Stollery, J.L.
Hypersonic viscous interaction - an experimental investigation of the flow over flat plates at incidence and around an expansion corner. Aerospace Res. Cited by: 8. Fundamentals of Aircraft and Rocket Propulsion - Ebook written by Ahmed F. El-Sayed. Read this book using Google Play Books app on your PC, android, iOS devices.
Download for offline reading, highlight, bookmark or take notes while you read 5/5(1). Ramjet Nozzle Analysis for Transport Aircraft Configuration for Sustained Hypersonic Flight Article (PDF Available) in Applied Sciences 8(4) April with 2, Reads How we measure 'reads'.
Shown in Fig. is the hypersonic strong viscous interaction at the leading edge of the flat plate to create induced pressure zone.
Since there is a considerable pressure change at the leading edge region the analysis of the boundary layer in hypersonic flow must be quite different from the classical approach.
In the framework of the PVSL theory, systematic numerical solutions of some two- and three-dimensional hypersonic viscous gas flow problems past blunt bodies for a wide range of Reynolds numbers and body shape are obtained; the accuracy and the applicability range of the suggested model are estimated on the basis of comparisons with theoretical Cited by: 1.
A computational study of hypersonic air ow over a three-dimensional blunt leading edge is carried out to investigate the energy deposition due to an arc discharge along the surface.
The discharge is the result of an imposed potential di erence between two ush-mounted electrodes. The energy deposition is the result of Joule heating, which is. Gas turbine engines (GTEs) for aircraft GTE have undergone continual evolution and improvement since their introduction during World War II.
As shown in Figurefundamental engine performance parameters have been significantly r, there remains substantial potential for improvement beyond the current state of the art for fielded military engines, which must undergo.
Great efforts have been dedicated during the last decades to the research and development of hypersonic aircrafts that can fly at several times the speed of sound. These aerospace vehicles have revolutionary applications in national security as advanced hypersonic weapons, in space exploration as reusable stages for access to low Earth orbit, and in commercial aviation as fast long-range Cited by: Hypersonic Flow Hypersonic Vehicles Effects of High Mach Number Effects of High Temperature Viscous Hypersonic Flow Effects of Low Density Approximate Analyses of Inviscid Hypersonic Flow Aerodynamic Heating FTT: Hypersonic Flight Testing Scramjet Nozzles 46th AIAA/ASME/SAE/ASEEJoint Propulsion Conference&Exhibit Integration with hypersonic vehicle Three-dimensional vehicle with triangular panels Propulsion ﬂowpath modeled as two-dimensional Vogel, J.
M., Kelkar, A. G., Inger, G., Whitmer, C., Sidlinger, A., and Viscous solution Approximatelycells Quasi-1D. The opening paragraph of the Statement of Task indicated that the committee should concentrate on the “strategy and content” of the Air Force HyTech Program (see Box for a summary of the program and Appendix B for a detailed description).
Part 1 of the Statement of Task asked the committee to focus on the “technologies needed to demonstrate a hypersonic, air-breathing missile concept. Viscous Hypersonic Flow Effects of Low Density Approximate Analyses of Inviscid Hypersonic Flow Aerodynamic Heating FTT: Hypersonic Flight Testing Summary of Lift and Drag Theories References Problems 4 Propulsion Introduction The Concept of Pages: THREE-DIMENSIONAL HYPERSONIC FLOW SEPARATION OVER SMALL TOPOLOGICAL FEATURES by Anqing Xu A Thesis Presented to the Graduate and Research Committee of Lehigh University in Candidacy for the Degree of Master of Science m.
Numerical thermal analyses that contributed to the elimination of turbine blade firtree cracks in the Space Shuttle Main Engine High Pressure Fuel Turbopump turbine A full Navier-Stokes analysis of a three dimensional hypersonic mixed compression inlet.
JEFFERY Optimized supersonic exhaust nozzles for hypersonic propulsion. NICKERSON. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Aircraft " ~ ' ~ ~ ~ ~ l k forebody. compression ~ - 'Aircraft surface afterbody nozzle Fig.
Hypersonic vehicle with a n a i r b r e a t h i n g propulsion system. was not predicted by the wind-tunnel data base, requiring a bodyflap deflection almost twice that predicted based on the Aerodynamic Design Data Book .To efficiently model fluid-thermal-structural problems for thermal protection design of hypersonic vehicles, a framework of Hypersonic Computational Coupling Dynamics (HyCCD) software integrates an independently developed program solving hypersonic aerthermodynamic simulation with a finite element analysis professional software.
With the mathematical and physical description of multi-physics Cited by: 1.