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Hypersonic Curved Compression Inlet And Its Inverse Design
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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 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.
Book Synopsis Key Basic Scientific Problems on Near-Space Vehicles by : Shanyi Du
Download or read book Key Basic Scientific Problems on Near-Space Vehicles written by Shanyi Du and published by Springer Nature. This book was released on 2023-04-02 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book mainly introduces the research overview, research results, and follow-up prospects of “Key Basic Scientific Problems on Near-Space Vehicles”, a major research plan of National Natural Science Foundation of China (hereinafter referred to as the Plan). The Plan is the first systematic basic hypersonic research program in China. From its inception in 2007 to its successful completion in 2016, the Plan lasted nine years, funded a total of 173 projects, and the funding totaled 190 million yuan. From the perspective of major national needs and scientific discipline development, the book focuses on four key scientific issues: aerodynamics in a near-space flight environment; advanced propulsion theories and methods; ultralight materials/structures, thermal environment prediction and thermal protection; and intelligent autonomous control theories and methods for hypersonic vehicles. The book also demonstrates China’s systematic and innovative achievements in interdisciplinary theories and methods and innovative techniques, paving the way for a distinctively Chinese basic research framework and further breakthroughs of near-space hypersonic vehicles.
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723796593 Total Pages :68 pages Book Rating :4.7/5 (965 download)
Book Synopsis Advanced Technology Inlet Design, Nra 8-21 Cycle II: Draco Flowpath Hypersonic Inlet Design by : National Aeronautics and Space Adm Nasa
Download or read book Advanced Technology Inlet Design, Nra 8-21 Cycle II: Draco Flowpath Hypersonic Inlet Design written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-18 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report outlines work performed in support of the flowpath development for the DRACO engine program. The design process initiated to develop a hypersonic axisymmetric inlet for a Mach 6 rocket-based combined cycle (RBCC) engine is discussed. Various design parametrics were investigated, including design shock-on-lip Mach number, cone angle, throat Mach number, throat angle. length of distributed compression, and subsonic diffuser contours. Conceptual mechanical designs consistent with installation into the D-21 vehicle were developed. Additionally, program planning for an intensive inlet development program to support a Critical Design Review in three years was performed. This development program included both analytical and experimental elements and support for a flight-capable inlet mechanical design.Sanders, Bobby W. and Weir, Lois J.Marshall Space Flight CenterHYPERSONIC INLETS; DESIGN ANALYSIS; ROCKET-BASED COMBINED-CYCLE ENGINES; ROCKET ENGINE DESIGN; FLOW DISTRIBUTION; THROATS; MACH NUMBER; PROJECT PLANNING; FUNCTIONAL DESIGN SPECIFICATIONS
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 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 Effect Of Micro-vortex Generator In Hypersonic Inlet by : Vivek V. Kumar
Download or read book Effect Of Micro-vortex Generator In Hypersonic Inlet written by Vivek V. Kumar and published by LAP Lambert Academic Publishing. This book was released on 2012-06 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: The recent advances in aerospace vehicle technology demands the best possible propulsive balance to provide better thrust and minimum drag. Air-breathing engines are the best choice for the propulsion due to its minimum weight. The efficiency of such engines depend upon the quality of air entering for combustion. This book provides complete flow analysis of both pure inline-compression and mixed-compression inlets. Two dimensional simulations were carried out with SST k- model using FLUENT. The boundary layer formed inner side of the engine had an adverse pressure gradient on the ramp producing a boundary layer separation. Due to this the boundary layer thickens and the static pressure starts to decrease whose effect leads till the trailing edge of inlet. Small wedge shaped Micro-Vortex Generator (MVG) inside the inlet smoothen the generated shock-boundary layers and thereby an efficient compression is obtained . The analysis should help shed some light on hypersonic inlet design optimization at off-design condition and should be especially useful to researchers and academicians in the field of Aerospace Engineering."
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 On the Design of Hypersonic Inward-Turning Inlets by :
Download or read book On the Design of Hypersonic Inward-Turning Inlets written by and published by . This book was released on 2007 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: A family of dual-axis compression, high-contraction-ratio, inward-turning inlets has been designed to achieve a desired shock structure and aerodynamic performance at Mach 6. Computational simulations of the internal inlet flowfield were performed using the research code FDL3DI. These solutions are an integrated part of the inlet design methodology and offer insight into the fundamental fluid phenomenology. The effects of viscous/inviscid interactions, namely swept-shock/turbulent boundary layer interactions are discussed. Additionally, the importance of complementary computational fluid dynamics (CFD) to the experimental work as part of the integrated hypersonic inlet design process is also addressed.
Book Synopsis An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers by : John F. Stroud
Download or read book An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers written by John F. Stroud and published by . This book was released on 1965 with total page 110 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 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:
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 Hypersonic Inlet Design Considerations by : James G. Snyder
Download or read book Hypersonic Inlet Design Considerations written by James G. Snyder and published by . This book was released on 1993 with total page 310 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Application of a Nonsimilar Laminar Boundary Layer Analysis to Hypersonic Inlet Compression Surfaces by : Dennis Sedlock
Download or read book The Application of a Nonsimilar Laminar Boundary Layer Analysis to Hypersonic Inlet Compression Surfaces written by Dennis Sedlock and published by . This book was released on 1966 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the results of an investigation in which the Smith and Clutter nonsimilar laminar boundary layer analysis is compared to experimental data and a modified linearized similar solution on typical hypersonic two-dimensional and axisymmetric inlet compression surfaces. The representative cases presented have a Mach number range of 11.6 to 16.87 and a unit Reynolds number of 60,000 to 400,000. For these conditions on the models investigated, the nonsimilar solution was found to treat transverse curvature as a first rather than a second order effect. Such factors as the input nondimensional boundary layer thickness, the distance between stations along the surface, and the selection of reference conditions were found to have an effect on the accuracy of the solution. The method showed satisfactory agreement with experimental data and the modified similar solution. Although not prohibitively long, the length of computer time suggests that the program should be used as a final design analysis tool rather than being applied in preliminary design stages. The detailed output of various quantities in the viscous layer makes the program particularly useful where temperature and velocity profiles are required. (Author).
Book Synopsis Hypersonic Vehicles by : Giuseppe Pezzella
Download or read book Hypersonic Vehicles written by Giuseppe Pezzella and published by BoD – Books on Demand. This book was released on 2019-10-02 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the aviation field there is great interest in high-speed vehicle design. Hypersonic vehicles represent the next frontier of passenger transportation to and from space. However, several design issues must be addressed, including vehicle aerodynamics and aerothermodynamics, aeroshape design optimization, aerodynamic heating, boundary layer transition, and so on. This book contains valuable contributions focusing on hypervelocity aircraft design. Topics covered include hypersonic aircraft aerodynamic and aerothermodynamic design, especially aeroshape design optimization, computational fluid dynamics, and scramjet propulsion. The book also discusses high-speed flow issues and the challenges to achieving the dream of affordable hypersonic travel. It is hoped that the information contained herein will allow for the development of safe and efficient hypersonic vehicles.
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 Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Time Accurate Computation of Unsteady Hypersonic Inlet Flows with a Dynamic Flow Adaptive Mesh by : D. McRae
Download or read book Time Accurate Computation of Unsteady Hypersonic Inlet Flows with a Dynamic Flow Adaptive Mesh written by D. McRae and published by . This book was released on 1998 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Completed research is reported for an dynamic numerical investigation of unsteady flow in supersonic and hypersonic aircraft inlets. An explicit dynamic solution adaptive mesh computational code was further developed and used to obtain dynamic solutions for an axisymmetric mixed compression inlet and a generic dual mode scramjet inlet isolator diffuser combination. To improve robustness, an existing implicit code was modified for time accuracy and the solution adaptive mesh algorithm was installed. The inlet unstart phenomenon was simulated through perturbation of freestream and downstream conditions (axisymmetric inlet) and through downstream throttling for the dual mode 3-D configuration. Axisymmetric unstart could be induced by a 10% freestream temperature increase or a 5% backpressure increase. Comparison of the results with experiment, where available, indicate that stability margins assessed through inviscid design or quasi-steady experiment may need revision when dynamics are considered. Conclusions are drawn concerning specifics of the flow phenomena and directions for future research are suggested. Lack of highly resolved dynamic experimental data is a pacing item and will prevent full verification of future work.
