Добірка наукової літератури з теми "Supersonic air inlet"
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Статті в журналах з теми "Supersonic air inlet"
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.
Повний текст джерелаZhang, 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.
Повний текст джерелаVnuchkov, 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.
Повний текст джерелаVinogradov, 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.
Повний текст джерелаChen, 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.
Повний текст джерелаFreskos, 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.
Повний текст джерелаCao, 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.
Повний текст джерелаFerrero, 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.
Повний текст джерелаUtomo, 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.
Повний текст джерелаEzrokhi, 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.
Повний текст джерелаДисертації з теми "Supersonic air inlet"
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.
Повний текст джерелаNajafiyazdi, 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.
Повний текст джерелаThe 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.
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.
Повний текст джерелаThe 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.
Книги з теми "Supersonic air inlet"
Trefny, Charles J. Low-speed performance of an axisymmetric, mixed-compression, supersonic inlet with auxiliary inlets. Cleveland, Ohio: Lewis Research Center, 1986.
Знайти повний текст джерелаPowell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.
Знайти повний текст джерелаPowell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.
Знайти повний текст джерелаPowell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.
Знайти повний текст джерелаInlets for supersonic missiles. Washington, D.C: American Institute of Aeronautics and Astronautics, 1990.
Знайти повний текст джерелаHolland, 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.
Знайти повний текст джерелаFisher, S. A. Internal performance of a variable ramp mixed compression intake at Mach 3.05. Melbourne, Vic: Aeronautical Research Laboratories, 1985.
Знайти повний текст джерелаW, 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.
Знайти повний текст джерелаW, 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.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration., ed. Minimum weight design of a generic axisymmetric inlet. [Washington, DC]: National Aeronautics and Space Administration, 1996.
Знайти повний текст джерелаТези доповідей конференцій з теми "Supersonic air inlet"
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.
Повний текст джерелаTUDOSIE, 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.
Повний текст джерелаKarpuzcu, 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.
Повний текст джерелаTudosie, 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.
Повний текст джерелаNakayama, 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.
Повний текст джерелаMiki, 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.
Повний текст джерелаSonoda, 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.
Повний текст джерелаCai, 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.
Повний текст джерелаFreskos, 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.
Повний текст джерелаRan, 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.
Повний текст джерела