Download or read book Numerical Investigation and Flow Interactions of a Mixed compression Hypersonic Inlet written by Pierre-Andre Bes and published by . This book was released on 2014 with total page 163 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical investigation of a fixed geometry mixed-compression scramjet inlet is presented in this paper to illustrate the compression process and flow interactions of a hypersonic inlet prior to supersonic combustion. Through the use of an AUSM (Advection Upstream Splitting Method) differencing scheme, applied for both inviscid and turbulent scenarios, this analysis explores the complex phenomena associated with hypersonic flows such as shock-shock and shock-boundary layer interactions. Particular attention is placed in the vicinity of the inlet throat area, where such interactions may cause flow separation and give rise to further complications such as inlet unstart. The inlet geometry is a modified version of the hydrogen-fueled axisymmetric scramjet used on the Hypersonic Flying Laboratory (HFL) named "Kholod", designed and tested by NASA and the Central Institute of Aviation Motors (CIAM) on February 12, 1998. The inlet is computationally solved using the commercial software FLUENT 6.3 and the computational grids were generated using the grid generator GAMBIT 2.4.6. Grid nodes were clustered near the critical flow path areas in order to accurately capture any viscous interactions within the flow field. Solutions presented in this paper assumed free stream properties equivalent to an altitude of 10,000 meters, at 0 degree angle of attack, with Mach numbers of 5, 7, and 9, all solved through both inviscid and turbulent models.

Download or read book Experimental Investigation of a Large scale Two dimensional Mixed compression Inlet System written by Norman D. Wong and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.

Download or read book Hypersonic Curved Compression Inlet and Its Inverse Design written by Kunyuan Zhang and published by Springer Nature. This book was released on 2020-01-22 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents systematic research results on curved shock wave-curved compression surface applied to the compression surface design of supersonic–hypersonic inlet, which is a brand new inlet design. The concept of supersonic inlet curved compression discussed originated from the author’s research at the Deutsches Zentrum fur Luft- und Raumfahrt (DLR SM-ES) in the early 1990s. This book introduces the research history, working characteristics, performance calculation and aerodynamic configuration design method of this compression mode in detail. It also describes method of estimating the minimum drag in inlet and drag reduction effect of curved compression and proposes a new index for evaluating unit area compression efficiency of the inlet. Further, it reviews the relevant recent research on curved compression. As such it is a valuable resource for students, researchers and scientists in the fields of hypersonic propulsion and aeronautics.

Download or read book Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the Rplus2d Code written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-29 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A two-dimensional computational code, PRLUS2D, which was developed for the reactive propulsive flows of ramjets and scramjets, was validated for two-dimensional shock-wave/turbulent-boundary-layer interactions. The problem of compression corners at supersonic speeds was solved using the RPLUS2D code. To validate the RPLUS2D code for hypersonic speeds, it was applied to a realistic hypersonic inlet geometry. Both the Baldwin-Lomax and the Chien two-equation turbulence models were used. Computational results showed that the RPLUS2D code compared very well with experimentally obtained data for supersonic compression corner flows, except in the case of large separated flows resulting from the interactions between the shock wave and turbulent boundary layer. The computational results compared well with the experiment results in a hypersonic NASA P8 inlet case, with the Chien two-equation turbulence model performing better than the Baldwin-Lomax model. Kapoor, Kamlesh and Anderson, Bernhard H. and Shaw, Robert J. Glenn Research Center NASA-TM-106580, E-8840, NAS 1.15:106580 RTOP 537-02-23...

Download or read book Numerical Simulation of a Mixed compression Supersonic Inlet Flow written by Joongkee Chung and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Shock Wave Boundary Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.

Download or read book Numerical Investigation of Shock vortex Interaction in Hypersonic Thermochemical Non equilibrium Flow written by Satoru Yamamoto and published by . This book was released on 1997 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Flow Fields Within Large scale Hypersonic Inlet Models written by A. Vernon Gnos and published by . This book was released on 1973 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical and experimental investigations were conducted to determine the internal flow characteristics in model passages representative of hypersonic inlets for use at Mach numbers to about 12. The passages were large enough to permit measurements to be made in both the core flow and boundary layers. The analytical techniques for designing the internal contours and predicting the internal flow-field development accounted for coupling between the boundary layers and inviscid flow fields by means of a displacement-thickness correction. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide high internal performance with an approximately uniform static-pressure distribution at the throat station. The models were tested in the Ames 3.5-Foot Hypersonic Wind Tunnel at a nominal free-stream Mach number of 7.4 and a unit free-stream Reynolds number of 8.86 X one million per meter.

Download or read book Experimental Investigation of a Large Scale Two dimensional Mixed compression Inlet System written by Warren E. Anderson and published by . This book was released on 1970 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Hypersonic Mixed compression Inlet Shock induced Combustion Ramjets written by Derrick Alexander and published by . This book was released on 2006 with total page 360 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study investigates the performance and flow field features of a mixed-compression inlet shock-induced combustion ramjet (shcramjet). In a shcramjet, oncoming air is compressed with shocks in the inlet and then further compressed and mixed with hydrogen fuel in a duct prior to shock-induced combustion and expansion of the combustion products through a divergent nozzle to provide thrust. Numerical studies are undertaken using the WARP code that solves the Favre-averaged Navier-Stokes equations closed by the Wilcox k-o turbulence model. Hydrogen/air combustion is solved via the twenty reaction, nine species combustion model of Jachimowski. Mixing augmentation through the use of cantilevered ramp injector arrays on opposite shcramjet inlet walls is studied and the influence of relative array locations is quantified. Increased spanwise distance between adjacent injectors on opposite walls allows for increased jet penetration and fuel distributions in the center of the engine duct. Chemically reacting studies verify an air buffer is created between the fuel and walls that suppresses premature ignition while still allowing for an air based mixing efficiency of up to 0.46-0.54. Combustion is produced over aerodynamic wedges with the spatial flow variation dictating both detonation and shock-induced combustion can be present over constant angle wedges. The initial inlet angle must be as high as possible, while avoiding premature ignition, to generate the pressure in the combustor needed for significant positive thrust. Thrust production from combustion is found to be insensitive to wedge angle if combustion is initiated across the cross-sectional area. Strong recirculation regions are formed via shock/boundary layer interactions in the confined engine duct. Mitigation of the recirculation is demonstrated with correct placement of the nozzle expansion in conjunction with air blowing in the boundary layer at a mass flow rate on the order of that of the fuel injection. For flight at Mach 11 the mixed-compression inlet shcramjet is found to generate a specific impulse of 683 s in the simulation of a realistic three-dimensional flow field.

Download or read book Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3 8 written by John H. Lundell and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Shock Wave Interactions written by Konstantinos Kontis and published by Springer. This book was released on 2018-03-28 with total page 408 pages. Available in PDF, EPUB and Kindle. Book excerpt: This edited monograph contains the proceedings of the International Shock Interaction Symposium, which emerged as an heir to both the Mach Reflection and Shock Vortex Interaction Symposia. These scientific biannual meetings provide an ideal platform to expose new developments and discuss recent challenges in the field of shock wave interaction phenomena. The goal of the symposia is to offer a forum for international interaction between young and established scientists in the field of shock and blast wave interaction phenomena. The target audience of this book comprises primarily researchers and experts in the field of shock waves, but the book may also be beneficial for young scientists and graduate students alike.

Download or read book Basic Research and Technologies for Two Stage to Orbit Vehicles written by Dieter Jacob and published by John Wiley & Sons. This book was released on 2006-03-06 with total page 683 pages. Available in PDF, EPUB and Kindle. Book excerpt: Focusing on basic aspects of future reusable space transportation systems and covering overall design, aerodynamics, thermodynamics, flight dynamics, propulsion, materials, and structures, this report presents some of the most recent results obtained in these disciplines. The authors are members of three Collaborative Research Centers in Aachen, Munich and Stuttgart concerned with hypersonic vehicles. A major part of the research presented here deals with experimental and numerical aerodynamic topics ranging from low speed to hypersonic flow past the external configuration and through inlet and nozzle. Mathematicians and engineers jointly worked on aspects of flight mechanics like trajectory optimization, stability, control and flying qualities. Structural research and development was predominantly coupled to the needs for high temperature resistant structures for space vehicles.

Download or read book Hypersonic Inlet With Plasma Induced Compression Postprint written by and published by . This book was released on 2006 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: A path-finding experimental investigation has been successfully accomplished to show the combined effect of an electromagnetic perturbation and viscous-inviscid interaction is a viable mechanism for improving hypersonic inlet performance. The plasma-induced compression is produced by a direct current discharge from electrodes embedded in the sidewalls of a rectangular constant cross-sectional area inlet. This repeatable compression acts as the sidewall compression of a variable area inlet but without the parasitic effect when deactivated. The accompanying numerical simulation is first calibrated with the measured Pitot pressures and then used to evaluate the overall flow structure within the inlet. The magneto-fluid-dynamics interaction is found to be unsteady and characterized with low amplitude and high frequency fluctuations. The validated result reveals that a plasma generating power supply of 19.12 watts per centimeter of electrode length produces an 11.6% pressure rise at the inlet exit.

Download or read book Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the RPLUS2D Code written by Kamlesh Kapoor and published by . This book was released on 1994 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book New Trends in Fluid Mechanics Research written by F. G. Zhuang and published by Springer Science & Business Media. This book was released on 2009-04-24 with total page 764 pages. Available in PDF, EPUB and Kindle. Book excerpt: This volume is the proceedings of the Fifth International Conference on Fluid Mechanics (ICFM-V), the primary forum for the presentation of technological advances and research results in the fields of theoretical, experimental, and computational Fluid Mechanics. Topics include: flow instability and turbulence, aerodynamics and gas dynamics, industrial and environmental fluid mechanics, biofluid mechanics, geophysical fluid mechanics, plasma and magneto-hydrodynamics, and others.