Relevant bibliographies by topics / Supersonic air inlet

Academic literature on the topic 'Supersonic air inlet'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Supersonic air inlet"

1

TUDOSIE, Alexandru-Nicolae, Emanuel DUMITRU, and Marius-Alin ASPRA. "CONTROL LAW FOR AN AIRCRAFT SUPERSONIC AIR INLET WITH INTERNAL COMPRESSION." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 21, no. 1 (October 8, 2019): 199–208. http://dx.doi.org/10.19062/2247-3173.2019.21.27.

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Zhang, Yue, Hui-jun Tan, Yi Zhuang, and De-peng Wang. "Morphing Supersonic Inlet with Deforming Air Cell." Journal of Propulsion and Power 31, no. 2 (March 2015): 583–91. http://dx.doi.org/10.2514/1.b35425.

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3

Vnuchkov, D. A., V. I. Zvegintsev, and D. G. Nalivaychenko. "Investigation of Throttling Characteristics in Supersonic Polyclinic Inlet." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 2 (125) (April 2019): 21–33. http://dx.doi.org/10.18698/0236-3941-2019-2-21-33.

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This paper presents an experimental investigation of throttling characteristics of a multi-wedge air inlet of a wind tunnel built for flat flow field at M = 2.5. The experiments were performed in a wind tunnel at M numbers of 2.55, 3.05 and 4.05. Results of numerical simulation of the flow in the air inlet, where air flow restriction was implemented by additional heating of the flow in the channel past the air inlet, are given for comparison. Experimental throttling characteristics are in good agreement with the values obtained from computations
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Vinogradov, Viacheslav A., Yurii M. Shikhman, and Corin Segal. "A Review of Fuel Pre-injection in Supersonic, Chemically Reacting Flows." Applied Mechanics Reviews 60, no. 4 (July 1, 2007): 139–48. http://dx.doi.org/10.1115/1.2750346.

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Developing an efficient, supersonic combustion-based, air breathing propulsion cycle operating above Mach 3.5, especially when conventional hydrocarbon fuels are sought and particularly when liquid fuels are preferred to increase density, requires mostly effective mechanisms to improve mixing efficiency. One way to extend the time available for mixing is to inject part of the fuel upstream of the vehicle’s combustion chamber. Injection from the wall remains one of the most challenging problems in supersonic aerodynamics, including the requirement to minimize impulse losses, improve fuel-air mixing, reduce inlet∕combustor interactions, and promote flame stability. This article presents a review of studies involving liquid and, in selected cases, gaseous fuel injected in supersonic inlets or in combustor’s insulators. In all these studies, the fuel was injected from a wall in a wake of thin swept pylons at low dynamic pressure ratios (qjet∕qair=0.6–1.5), including individual pylon∕injector geometries and combinations in the inlet and combustor’s isolator, a variety of injection conditions, different injectants, and evaluated their effects on fuel plume spray, impulse losses, and mixing efficiency. This review article cites 47 references.
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Chen, Haoying, Haibo Zhang, Zhihua Xi, and Qiangang Zheng. "Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback." International Journal of Aerospace Engineering 2020 (January 4, 2020): 1–13. http://dx.doi.org/10.1155/2020/5313941.

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In order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynamic and static effects of the bleeding flow rate on the normal shock position were investigated. The transfer function was identified, and simultaneously the paper carried out a comprehensive study of inlet and engine integrated model, which is established based on the inlet shock position model and engine component level model. The relationship between normal shock position and total pressure recovery coefficient has been taken into consideration in this model. Based on the inlet and engine integrated model, the closed-loop control simulation of normal shock position is carried out. The results show that the model could resist the disturbance of the inlet flow and keep the inlet and engine matching operation point stable near the optimal value.
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6

Freskos, G., and O. Penanhoat. "Numerical Simulation of the Flow Field Around Supersonic Air-Intakes." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 116–23. http://dx.doi.org/10.1115/1.2906780.

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The demand for efficiency in today’s and in future civil aircraft is such that experimental studies alone do not suffice to optimize aircraft aerodynamics. In this context, much effort has been spent in the past decade to develop numerical methods capable of reproducing the phenomena that occur in the engine flow field. This paper presents some studies in Computational Fluid Dynamics related to supersonic inlets. Two approaches are considered. First, there is a need for a code capable of calculating in a cost-efficient way the entire flow field around a two-dimensional or three-dimensional inlet, e.g., to perform parametric studies. To this effect, a computing method based on grid construction by mesh generator dedicated to inlet shapes and on the discretization of the unsteady Euler equations with an explicit upwind scheme was developed. The treatment of complex geometries led us to adopt a multiblock grid approach. Therefore particular attention was paid to the treatment of the boundary conditions between the different domains. Second, there is a need for a code that can capture local phenomena in order to get a better understanding of inlet behavior (shock/shock, shock/boundary layer interactions, etc.). To this effect a two-dimensional turbulent Navier-Stokes code is used. The two-equation k-ε turbulence model included in the program seems to be one of the most successful models for calculating flow realistically. Correction of the near-wall influence extends its capability to complex flow configurations, e.g., those with separated zones.
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7

Cao, Da Min, Hong Yang Lv, Xing Yuan Zhang, and Sheng Bin Hu. "Numerical Simulation of the Supersonic Inlet Flow Field." Applied Mechanics and Materials 29-32 (August 2010): 2119–23. http://dx.doi.org/10.4028/www.scientific.net/amm.29-32.2119.

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The 2-D internal steady flow of the scramjet inlet-isolator was numerically simulated by the CFD method. The static pressure contours of the scramjet inlet-isolator under different boundary thickness and different back pressure were given. The numerical simulation results of two kinds of reasons which make the inlet un-start are obtained. One is the boundary layer thickness and another is the high back pressure at the exit of the isolator. When the boundary layer thickness increased, air can not smoothly flow into the inlet isolator and caused inlet un-start. Sameness along with the back pressure rise, have the phenomenon of inlet un-start, too. But the reason of un-start is disaffiliate. In the text analyzed the reasons of un-start phenomenon which from two different perspectives on the problem.
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8

Ferrero, Andrea. "Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed." Aerospace 7, no. 3 (March 19, 2020): 32. http://dx.doi.org/10.3390/aerospace7030032.

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Supersonic inlets are a key component of present and future air-breathing propulsion systems for high-speed flight. The inlet design is challenging because of several phenomena that must be taken under control: shock waves, boundary layer separation and unsteadiness. Furthermore, the intensity of these phenomena is strongly influenced by the working conditions and so active control systems can be particularly useful in off-design conditions. In this work, a mixed compression supersonic inlet with a double wedge ramp is considered. The flow field was numerically investigated at different values of Mach number. The simulations show that large separations appear at the higher Mach numbers on both the upper and lower walls of the duct. In order to improve the performances of the inlet two different control strategies were investigated: plasma actuators and bleed. Different locations of the plasma actuator are considered in order to also apply this technology to configurations with a diverter which prevents boundary layer ingestion. The potential of the proposed solutions is investigated in terms of total pressure recovery, flow distortion and power consumption.
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Utomo, Muhammad Adnan, and Romie Oktavianus Bura. "Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft." INSIST 2, no. 2 (January 25, 2019): 104. http://dx.doi.org/10.23960/ins.v2i2.90.

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Inward-turning external compression intake is one of the hybrid intakes that employs both external and internal compression intakes principle. This intake is commonly developed for hypersonic flight due to its efficiency and utilizing fewer shockwaves that generate heat. Since this intake employ less shockwaves, this design can be applied for low supersonic (Mach 1.4 - 2.5) intakes to reduce noise generated from the shockwaves while maintaining the efficiency. Other than developing the design method, a tool is written in MATLAB language to generate the intake shape automatically based on the desired design requirement. To investigate the intake design tool code and the performance of the generated intake shape, some CFD simulation were performed. The intake design tool code can be validated by comparing the shockwave location and the air properties in every intake's stations. The performance parameters that being observed are the intake efficiency, flow distortion level at the engine face, and the noise level generated by the shockwaves. The design tool written in MATLAB is working as intended. Two dimensional axisymmetric CFD simulations validation has been done and the design meets the minimum requirement. As for the 3D inlet geometry, with a little modification on diffuser and equipping vent to release the buildup pressure, the inlet has been successfully met the military standard on inlet performance (MIL-E-5007D). This design method also has feature to fit every possible throat cross sectional shapes and has been proven to work as designed.Keywords— Inward-turning, Supersonic, Engine Intakes, Low- noise, Design Method
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Ezrokhi, Yu A., and E. A. Khoreva. "Assessing the Impact of the Inlet Total Pressure Distortion on the Turbofan Thrust." Mechanical Engineering and Computer Science, no. 1 (March 3, 2018): 19–30. http://dx.doi.org/10.24108/0118.0001360.

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The paper considers techniques to develop a mathematical model using a method of «parallel compressors». The model is intended to estimate the impact of the air inlet distortion on the primary parameters of the aero-engine. The paper presents rated estimation results in the context of twin spool turbofan design for two typical cruiser modes of flight of the supersonic passenger jet. In estimation the base values σbase and the average values of the inlet ram recovery σave remained invariable. Thus, parametrical calculations were performed for each chosen relative value of the area of low-pressure region.The paper shows that an impact degree of the inlet distortion on the engine thrust for two modes under consideration is essentially different. In other words, if in the subsonic mode the impact assessment can be confined only to taking into account the influence of decreasing average values of the inlet total pressure, the use of such an assumption in the supersonic cruiser mode may result in considerable errors.With invariable values of the pressure recovery factor at the engine intake, which correspond to the speed of flight for a typical air inlet of external compression σbase, and average value σave, a parameter Δσuneven has the main effect on the engine thrust, and degree of this effect essentially depends on a difference between σave and σbase values.
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Dissertations / Theses on the topic "Supersonic air inlet"

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Malo-Molina, Faure Joel. "Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.

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To advance the design of hypersonic vehicles, high-fidelity multi-physics CFD is used to characterize 3-D scramjet flow-fields in two novel streamline traced configurations. The two inlets, Jaws and Scoop, are analyzed and compared to a traditional rectangular inlet used as a baseline for on/off-design conditions. The flight trajectory conditions selected are Mach 6 and a dynamic pressure of 1,500 psf (71.82 kPa). Analysis of these hypersonic inlets is performed to investigate distortion effects downstream with multiple single cavity combustors acting as flame holders, and several fuel injection strategies. The best integrated scramjet inlet/combustor design is identified. The flow physics is investigated and the integrated performance impact of the two innovative scramjet inlet designs is quantified. Frozen and finite rate chemistry is simulated with 13 gaseous species and 20 reactions for an Ethylene/air finite-rate chemical model. In addition, URANS and LES modeling are compared to explore overall flow structure and to contrast individual numerical methods. The flow distortion in Jaws and Scoop is similar to some of the distortion in the traditional rectangular inlet, despite design differences. The baseline and Jaws performance attributes are stronger than Scoop, but Jaws accomplishes this while eradicating the cowl lip interaction, and lessening the total drag and spillage penalties. The innovative inlets work best on-design, whereas for off-design, the traditional inlet is best. Early pressure losses and flow distortions in the isolator aid the mixing of air and fuel, and improve the overall efficiency of the system. Although the trends observed with and without chemical reactions are similar, the former yields roughly 10% higher mixing efficiency and upstream reactions are present. These show a significant impact on downstream development. Unsteadiness in the combustor increases the mixing efficiency, varying the flame anchoring and combustion pressure effects upstream of the step.
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2

Najafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.

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Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets.
The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for these parameters are derived for both subsonic and supersonic flow conditions. In the case of mass spillage from supersonic flows, the relations are exact. However, due to the complexity of flow field, the theory is an approximation for subsonic flows. Therefore, a correction factor is introduced which is determined from an empirical relation obtained from numerical simulations.
A methodology is also proposed to determine perforation size and distribution to achieve flow starting for a given inlet at a desired free-stream Mach number. The problem of shock stability inside a perforated inlet designed with the proposed method is also discussed.
The method is demonstrated for some test cases. Time-realistic CFD simulations and experimental results in the literature confirm the accuracy of the theory and the reliability of the proposed design methodology.
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Baig, Saood Saeed. "A simple moving boundary technique and its application to supersonic inlet starting /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112555.

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In this thesis, a simple moving boundary technique has been suggested, implemented and verified. The technique may be considered as a generalization of the well-known "ghost" cell approach for boundary condition implementation. According to the proposed idea, the moving body does not appear on the computational grid and is allowed to move over the grid. The impermeable wall boundary condition is enforced by assigning proper gasdynamic values at the grid nodes located inside the moving body close to its boundaries (ghost nodes). The reflection principle taking into account the velocity of the boundaries assigns values at the ghost nodes. The new method does not impose any particular restrictions on the geometry, deformation and law of motion of the moving body.
The developed technique is rather general and can be used with virtually any finite-volume or finite-difference scheme, since the modifications of the schemes themselves are not required. In the present study the proposed technique has been incorporated into a one-dimensional non-adaptive Euler code and a two-dimensional locally adaptive unstructured Euler code.
It is shown that the new approach is conservative with the order of approximation near the moving boundaries. To reduce the conservation error, it is beneficial to use the method in conjunction with local grid adaptation.
The technique is verified for a number of one and two dimensional test cases with analytical solutions. It is applied to the problem of supersonic inlet starting via variable geometry approach. At first, a classical starting technique of changing exit area by a moving wedge is numerically simulated. Then, the feasibility of some novel ideas such as a collapsing frontal body and "tractor-rocket" are explored.
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Books on the topic "Supersonic air inlet"

1

Trefny, Charles J. Low-speed performance of an axisymmetric, mixed-compression, supersonic inlet with auxiliary inlets. Cleveland, Ohio: Lewis Research Center, 1986.

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2

Powell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Powell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Powell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Inlets for supersonic missiles. Washington, D.C: American Institute of Aeronautics and Astronautics, 1990.

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6

Holland, Scott D. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Fisher, S. A. Internal performance of a variable ramp mixed compression intake at Mach 3.05. Melbourne, Vic: Aeronautical Research Laboratories, 1985.

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W, Wasserbauer Joseph, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Low-speed performance of an axisymmetric, mixed-compression, supersonic inlet with auxiliary inlets. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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W, Wasserbauer Joseph, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Low-speed performance of an axisymmetric, mixed-compression, supersonic inlet with auxiliary inlets. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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United States. National Aeronautics and Space Administration., ed. Minimum weight design of a generic axisymmetric inlet. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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Conference papers on the topic "Supersonic air inlet"

1

Vnuchkov, D. A., V. I. Zvegintsev, D. G. Nalivaychenko, V. I. Smoljaga, and A. V. Stepanov. "Off-design operation of supersonic polyclinic air inlet." In INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2018). Author(s), 2018. http://dx.doi.org/10.1063/1.5065221.

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TUDOSIE, Alexandru-Nicolae, and Vasile PRISACARIU. "SUPERSONIC AIR INLET FOR A HIGH VELOCITY PROPULSION SYSTEM." In SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE. Publishing House of “Henri Coanda” Air Force Academy, 2022. http://dx.doi.org/10.19062/2247-3173.2021.22.19.

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The paper aims to determine the optimal geometry, the control law and the operational limits of a supersonic air inlet; its operation control consists of its central cone positioning, with respect to the flight Mach number, keeping in sight the necessity of a suitable parameters’ distribution into engine’s combustion chamber. Inlet’s optimal architecture shall be determined (based on an algorithm regarding the maximization of the total pressure recovery), using basic planar geometry principles. Based on the optimal geometry of the inlet, its flow rate characteristic and its control law, as well as inlet’s operation limits were calculated and graphically represented.
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Karpuzcu, Irmak Taylan, Kemal Bulent Yuceil, Umit Poyraz, Ezgi Arisoy, Utku Olgun, and Hasan Tabanli. "Wind Tunnel Tests of Rectangular Supersonic Air Inlet at ITU." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-4424.

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Tudosie, Alexandru-Nicolae. "Control Law for the Air Inlet of a Supersonic Drone." In 2022 8th International Conference on Control, Decision and Information Technologies (CoDIT). IEEE, 2022. http://dx.doi.org/10.1109/codit55151.2022.9803926.

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Nakayama, Tomohiro, Tetsuya Sato, Masahiro Akatsuka, Atsushi Hashimoto, Takayuki Kojima, and Hideyuki Taguchi. "Investigation on Shock Oscillation Phenomenon in a Supersonic Air Inlet." In 41st AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-3094.

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Miki, Hajime, Masaharu Kameda, and Yasushi Watanabe. "Low Drag Design and Aerodynamic Performance Evaluation of Supersonic Air Inlet." In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3798.

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Sonoda, Toyotaka, Markus Olhofer, Toshiyuki Arima, and Bernhard Sendhoff. "A New Concept of a Two-Dimensional Supersonic Relative Inlet Mach Number Compressor Cascade." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59926.

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In this study, a numerical shape optimization method based on evolutionary algorithms coupled with a verified CFD solver has been applied to the ambitious target of a shock free 2-D supersonic inlet Mach number compressor cascade. The study is based on the DLR-PAV-1.5 supersonic compressor cascade designed by the pre-compression blading concept. The DLR cascade airfoil has been optimized using a verified CFD code. A superior performance of the optimized supersonic cascade with about 24% reduction of the total pressure loss coefficient compared to the original cascade has been realized. The flow mechanisms observable around the blade with improved performance and the resulting design concept are discussed in this paper.
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Cai, Feichao, and Xing Huang. "Influence of shield on supersonic inlet characteristics." In GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-299.

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For the supersonic inlet with shield plate, the internal and external flow integration calculation model is established. The influence of shield plate on the flow field parameter distribution of the supersonic inlet is studied by numerical method. The influence of shield plate length on the flow field and inlet performance is analyzed. The influence of shield plate on the aerodynamic performance of the body / inlet with abdominal layout is studied by comparing with the scheme without shield plate The influence of interference. The simulation results show that the shield plate can adjust the shock system configuration of the supersonic inlet and improve the angle of attack characteristics of the inlet. The length of the shield plate has a significant effect on the pre compression effect of the inlet air flow. Adding the shield plate can reduce the interference of the body on the inlet flow field.
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Freskos, G., and O. Penanhoat. "Numerical Simulation of the Flow Field Around Supersonic Air-Intakes." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-206.

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The demand for efficiency in today’s and in future civil aircraft is such that experimental studies alone do not suffice to optimize aircraft aerodynamics. In this context, much effort has been spent in the past decade to develop numerical methods capable of reproducing the phenomena that occur in the engine flow field. This paper presents some studies in Computational Fluid Dynamics related to supersonic inlets. Two approaches are considered. First, there is a need for code capable of calculating in a cost-efficient way the entire flow field around a 2D or 3D inlet, e.g. to perform parametric studies. To this effect, a computing method based on grid construction by mesh generator dedicated to inlet shapes and on the discretization of the unsteady Euler equations with an explicit upwind scheme was developed. The treatment of complex geometries led us to adopt a multiblock grid approach. Therefore particular attention was paid to the treatment of the boundary conditions between the different domains. Secondly, there is a need for code that can capture local phenomena in order to get a better understanding of inlet behaviour (shock/shock, shock/boundary layer interactions, etc.). To this effect a 2D turbulent Navier-Stokes code is used. The 2 equations k-ε turbulence model included in the program seems to be one of the most successful models for calculating flow realistically. Correction of the near-wall influence extends its capability to complex flow configurations, e.g. those with separated zones.
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10

Ran, Hongjun, and Dimitri Mavris. "Preliminary Design of a 2D Supersonic Inlet to Maximize Total Pressure Recovery." In AIAA 5th ATIO and16th Lighter-Than-Air Sys Tech. and Balloon Systems Conferences. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-7357.

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