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Numerical Investigation And Flow Interactions Of A Mixed Compression Hypersonic Inlet
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Book Synopsis Numerical Investigation and Flow Interactions of a Mixed-compression Hypersonic Inlet by : Pierre-Andre Bes
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.
Book Synopsis Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System by : Norman D. Wong
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.
Book Synopsis Hypersonic Curved Compression Inlet and Its Inverse Design by : Kunyuan Zhang
Download or read book Hypersonic Curved Compression Inlet and Its Inverse Design written by Kunyuan Zhang and published by Springer. This book was released on 2021-01-23 with total page 332 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.
Book Synopsis Experimental Investigation of a Large Scale, Two-dimensional, Mixed-compression Inlet System by : Warren E. Anderson
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:
Book Synopsis Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 by : John H. Lundell
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:
Book Synopsis Numerical Simulation of a Mixed-compression Supersonic Inlet Flow by : Joongkee Chung
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:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781792705748 Total Pages :30 pages Book Rating :4.7/5 (57 download)
Book Synopsis Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the Rplus2d Code by : National Aeronautics and Space Adm Nasa
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...
Book Synopsis Investigation of Flow Fields Within Large-scale Hypersonic Inlet Models by : A. Vernon Gnos
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.
Book Synopsis An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers: Data reduction program and tabulated experimental data by : J. F. Stroud
Download or read book An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers: Data reduction program and tabulated experimental data written by J. F. Stroud and published by . This book was released on 1965 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.
Book Synopsis Low-speed Performance of an Axisymmetric, Mixed-compression, Supersonic Inlet with Auxiliary Inlets by : Charles J. Trefny
Download or read book Low-speed Performance of an Axisymmetric, Mixed-compression, Supersonic Inlet with Auxiliary Inlets written by Charles J. Trefny and published by . This book was released on 1986 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Interactive, Design and Educational Tool for Supersonic External-compression Inlets by : Thomas J. Benson
Download or read book An Interactive, Design and Educational Tool for Supersonic External-compression Inlets written by Thomas J. Benson and published by . This book was released on 1994 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the RPLUS2D Code by : Kamlesh Kapoor
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:
Book Synopsis Hypersonic Mixed-compression Inlet Shock-induced Combustion Ramjets by : Derrick Alexander
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.
Book Synopsis Supersonic Inlet Investigation by : T. W. Tsukahira
Download or read book Supersonic Inlet Investigation written by T. W. Tsukahira and published by . This book was released on 1971 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reported herein are the results of an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests. The baseline models included a two-dimensional external compression inlet, a two-dimensional mixed compression inlet, and a half-axisymmetric external compression inlet. Alternate configurations for the external compression baseline inlets in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a non-uniform flow field, the later representing partial simulation of a vehicle flow field. Inlet steady state performance was characterized in terms of pressure recovery, pressure distortion, and turbulence levels at a simulated compressor face and immediately downstream of the inlet throat. In addition, detailed analysis and correlation of data obtained with high response dynamic instrumentation were made.
Book Synopsis Hypersonic Inlet With Plasma Induced Compression (Postprint). by :
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.
Book Synopsis Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 by : John H. Lundell
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 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An idealized axisymmetric, all-internal compression inlet was designed for a Mach number of 3.75. The objective of the design was to obtain a steady, one-dimensional transonic flow and a high over-all total-pressure recovery. Boundary-layer removal was employed in the vicinity of the inflection point of the supersonic contour. Static- and total-pressure fluctuations were measured in the transonic flow region. A total-pressure recovery of about 90 percent was obtained with a boundary-layerremoval mass-flow rate of 15 percent of the inlet mass-flow rate. The accompanying root-meansquare total-pressure fluctuation in the throat region was only 1 percent of the free-stream total pressure. The test Mach number was 3.80 and the Reynolds number based on inlet diameter was 2.63 times 10 to the 6th power. (Author).
Book Synopsis Experimental and Analytical Investigation of the Dynamic Response of a Supersonic Mixed-compression Inlet by : Joseph F. Wasserbauer
Download or read book Experimental and Analytical Investigation of the Dynamic Response of a Supersonic Mixed-compression Inlet written by Joseph F. Wasserbauer and published by . This book was released on 1968 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt:
