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Journal articles on the topic 'Supersonic speed conditions'

Author: Grafiati

Published: 5 June 2025

Last updated: 2 August 2025

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1

Aprovitola, Andrea, Oleksandr Dyblenko, Giuseppe Pezzella, and Antonio Viviani. "Aerodynamic Analysis of a Supersonic Transport Aircraft at Low and High Speed Flow Conditions." Aerospace 9, no. 8 (2022): 411. http://dx.doi.org/10.3390/aerospace9080411.

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The recent improvement of technology readiness level in aeronautics and the renewed demand for faster transportation are driving the rebirth of supersonic flight for commercial aviation. However, the design of a future supersonic aircraft is still very challenging due to the complexity of several problems, such as static stability performance during the acceleration phase from subsonic speeds to supersonic speeds. Additionally, the interest of scientific community in open source numerical platform as a valid tool for a reliable and affordable aerodynamic design is considerably growing. In this

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2

Ищенко, А. Н., В. В. Буркин, А. С. Дьячковский та ін. "Одиночное и совместное движение суперкавитирующих ударников в сверхзвуковом режиме в воде". Журнал технической физики 46, № 23 (2020): 22. http://dx.doi.org/10.21883/pjtf.2020.23.50343.18484.

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The research considers features of the underwater movement of single and two supercavitating strikers when simultaneous penetration into the water at speeds exceeding of sound speed. Conditions which provide non-destructive penetration into the water of strikers and their stable movement along an aiming trajectory at the transonic speed range has been developed. A stable cooperative movement of two strikers at the supersonic speed has been realized.

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Chudoba, B., G. Coleman, A. Oza, and P. A. Czysz. "What price supersonic speed? A design anatomy of supersonic transportation Part 1." Aeronautical Journal 112, no. 1129 (2008): 141–51. http://dx.doi.org/10.1017/s0001924000002074.

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Abstract The first generation of supersonic commercial transportation has seen three serious attempts to arrive at an economically and environmentally viable aircraft. The US B2707-200/300 design was cancelled early before a prototype could emerge; the Russian Tu-144 design succeeded to become the first supersonic transport but spanned only a few years of restricted airline service; the Anglo-French Concorde endured more than 27 glamorous airline service years until the last of its species was retired on 30 August 2003. This first generation was followed by a second generation of supersonic co

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Lou, Fangyuan, John Charles Fabian, and Nicole Leanne Key. "Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements." International Journal of Rotating Machinery 2018 (2018): 1–9. http://dx.doi.org/10.1155/2018/7281691.

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This paper investigates the aerodynamics of a transonic impeller using static pressure measurements. The impeller is a high-speed, high-pressure-ratio wheel used in small gas turbine engines. The experiment was conducted on the single stage centrifugal compressor facility in the compressor research laboratory at Purdue University. Data were acquired from choke to near-surge at four different corrected speeds (Nc) from 80% to 100% design speed, which covers both subsonic and supersonic inlet conditions. Details of the impeller flow field are discussed using data acquired from both steady and ti

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De Tavernier, Delphine, and Dominic von Terzi. "The emergence of supersonic flow on wind turbines." Journal of Physics: Conference Series 2265, no. 4 (2022): 042068. http://dx.doi.org/10.1088/1742-6596/2265/4/042068.

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Abstract The future generation of wind turbines will be characterised by longer and more flexible blades. These large wind turbines are facing higher Reynolds numbers, as a consequence of longer chord lengths and increased relative wind speeds. Higher tip speeds, however, also result in an increased Mach number. Although the maximum tip speed in steady design conditions may remain (well) below the critical value, the presence of turbulence, wind gusts, blade deflections, etc. in combination with the flow acceleration over the airfoil surface, may cause a significant increase in the velocity pe

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Aprovitola, Andrea, Pasquale Emanuele Di Nuzzo, Giuseppe Pezzella, and Antonio Viviani. "Aerodynamic Analysis of a Supersonic Transport Aircraft at Landing Speed Conditions." Energies 14, no. 20 (2021): 6615. http://dx.doi.org/10.3390/en14206615.

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Supersonic flight for commercial aviation is gaining a renewed interest, especially for business aviation, which demands the reduction of flight times for transcontinental routes. So far, the promise of civil supersonic flight has only been afforded by the Concorde and Tupolev T-144 aircraft. However, little or nothing can be found about the aerodynamics of these aeroshapes, the knowledge of which is extremely interesting to obtain before the development of the next-generation high-speed aircraft. Therefore, the present research effort aimed at filling in the lack of data on a Concorde-like ae

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Chai, Xiaochuan, Prahladh S. Iyer, and Krishnan Mahesh. "Numerical study of high speed jets in crossflow." Journal of Fluid Mechanics 785 (November 13, 2015): 152–88. http://dx.doi.org/10.1017/jfm.2015.612.

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Large-eddy simulation (LES) and dynamic mode decomposition (DMD) are used to study an underexpanded sonic jet injected into a supersonic crossflow and an overexpanded supersonic jet injected into a subsonic crossflow, where the flow conditions are based on the experiments of Santiago & Dutton (J. Propul. Power, vol. 13 (2), 1997, pp. 264–273) and Beresh et al. (AIAA J., vol. 43, 2005a, pp. 379–389), respectively. The simulations successfully reproduce experimentally observed shock systems and vortical structures. The time averaged flow fields are compared to the experimental results, and g

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8

Kanik Mittal and Sachin Srivastava. "SCRAMJET: Future High Speed Aircraft." Acceleron Aerospace Journal 3, no. 7 (2024): 785. https://doi.org/10.61359/11.2106-2476.

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In the current era of technological advancement, the scramjet has become one of the most conventional engines for achieving supersonic speeds in aircraft. The scramjet comprises three basic components: the inlet, combustor, and nozzle. Various fuels, such as Kerosene, JP-7, JP-8, hydrocarbon-based fuels, and hydrogen, have been used in scramjets, demonstrating distinct performance characteristics. Tests have shown that hydrocarbon-fueled scramjet engines can achieve a Mach number range of 3.5 to 7, while solid-fueled scramjets have the potential to achieve combustion efficiencies of 0.7–0.9. F

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9

Figat, Marcin, and Agnieszka Kwiek. "Aerodynamic optimisation of the rocket plane in subsonic and supersonic flight conditions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (2017): 2266–81. http://dx.doi.org/10.1177/0954410017723672.

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This paper presents the results of a numerical study of the aerodynamic shape of the Rocket Plane LEX. The Rocket Plane is a main part of the Modular Airplane System – MAS; a special vehicle devoted to suborbital tourist flights. The Rocket Plane was designed for subsonic and supersonic flight conditions. Therefore, the impact of the Mach number should be considered during the aerodynamic design of the Rocket Plane. The main goal of the investigation was to determine the sensitivity of the Rocket Plane aerodynamic characteristics to the Mach number during the optimisation of the LEX geometry.

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10

Xu, Xing, and Jun Hu. "Research on Aerodynamic Characteristics of Lateral Jet Control Technology." Advanced Materials Research 709 (June 2013): 253–56. http://dx.doi.org/10.4028/www.scientific.net/amr.709.253.

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This paper takes N-S equation as the basic control equation, selects turbulence model, and adopts the sliding mesh technology to conduct numerical simulation for the interference of missile jet flow and inflow on the flow field in different flow conditions. The results indicate that: the lift coefficient, drag coefficient and pressure center coefficient of missile body change with the changes of flowMach number and attack angle. The lift coefficient increases with the increase of Mach number in subsonic speed, decreases with the increase of Mach number in supersonic speed, and reaches a maximu

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Zhang, Tian, Deji Jing, Shaocheng Ge, Jiren Wang, Xi Chen, and ShuaiShuai Ren. "Dust removal characteristics of a supersonic antigravity siphon atomization nozzle." Advances in Mechanical Engineering 12, no. 12 (2020): 168781402097768. http://dx.doi.org/10.1177/1687814020977689.

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To improve the trapping efficiency of respiratory dust by aerodynamic atomization, reduce the energy consumption and the requirements for the working conditions of nozzles and maintain the health and safety of workers, a comparative experiment evaluating aerodynamic atomization dust removal characteristics was conducted with a self-developed supersonic siphon atomization nozzle, which utilizes a Laval nozzle as the core, and an existing ultrasonic atomization nozzle. The experimental results showed that the new type of nozzle, from the perspectives of droplet speed, conservation of water and p

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12

Han, Junhao, Lin He, and Zhengbang Wu. "Experimental investigation on evolution characteristics of high- and low-speed streaks in supersonic turbulent boundary layer." AIP Advances 12, no. 11 (2022): 115204. http://dx.doi.org/10.1063/5.0121259.

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High-speed and low-speed streak structures in the near wall region of a turbulent boundary layer with a Mach number of 3 are experimentally examined by employing the spatiotemporally resolved nanoparticle plane laser scattering technique. The time evolution characteristics of the high-speed and low-speed streaks in the supersonic turbulent boundary layer are systematically investigated through the speed field sequence results at various time intervals. The obtained results reveal that the dynamic behavior of the bands is chiefly represented by the translation along the flow direction. The proc

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13

Yu, Huicun, Bangying Tang, Haolin Ding, et al. "Airborne Quantum Key Distribution Performance Analysis under Supersonic Boundary Layer." Entropy 25, no. 3 (2023): 472. http://dx.doi.org/10.3390/e25030472.

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Airborne quantum key distribution (QKD) that can synergize with terrestrial networks and quantum satellite nodes is expected to provide flexible and relay links for the large-scale integrated communication network. However, the photon transmission rate would be randomly reduced, owing to the random distributed boundary layer that surrounding to the surface of the aircraft when the flight speed larger than Mach 0.3. Here, we investigate the airborne QKD performance with the BL effects. Furthermore, we take experimental data of supersonic BL into the model and compare the airborne QKD performanc

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Yan, Cheng, Wei Chen, and Zhenhua Zhao. "Experimental study on the high-speed impact of a sand particle on Ti–6Al–4V." Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology 234, no. 4 (2019): 632–46. http://dx.doi.org/10.1177/1350650119866046.

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When sand is ingested by a helicopter engine, it collides with the compressor blades at a high relative speed, causing severe erosion damage. A test was conducted on the high-speed impact of sand particles on the target of Ti–6Al–4 V alloy to enhance the understanding of high-speed impact damage mechanism. The test apparatus was used to create supersonic airflow, which was produced by normal temperature air flowing through a special Laval nozzle. The supersonic airflow produced the drag force to increase the velocity of sand particles up to about 400 m/s. The experiment demonstrated that fract

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15

Wang, J. J., and F. Chen. "On the start condition of a second-throat ejector-diffuser." Aeronautical Journal 100, no. 998 (1996): 321–26. http://dx.doi.org/10.1017/s0001924000067026.

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AbstractThe start condition of a second-throat ejector-diffuser (STED) system has been studied by solving the axisymmetric Navier-Stokes equations with a high order conservative supra-characteristics method (CSCM). According to the conventional concept, when a STED is started, the flow passing through the second-throat contraction should be supersonic so that the normal shock swallowing condition applying for a supersonic windtunnel holds. The present numerical results, however, suggest that a STED can be started with a normal shock forming ahead of the second-throat contraction because the hi

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16

Krishnan, Mithun, Anurag Ray, and Ravi Peetala. "Numerical Analysis of High Speed Flow Applications using Various Flux Schemes." Trends in Sciences 19, no. 18 (2022): 5813. http://dx.doi.org/10.48048/tis.2022.5813.

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Numerical analysis using computational fluid dynamics is an affordable and effective method with increasing relevance every day in research and engineering problems. Choosing an appropriate convective discretization scheme is paramount importance for obtaining more accurate solutions using CFD methods. The present study compares two commonly used numerical convective schemes, the upwind scheme of Advection Upstream Splitting Method (AUSM) and the central schemes of Kurganov-Noelle-Petrova and Kurganov-Tadmor scheme (K-T) have been made to find the better central scheme. These two schemes are v

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17

KINZIE, KEVIN W., and DENNIS K. McLAUGHLIN. "Aeroacoustic properties of supersonic elliptic jets." Journal of Fluid Mechanics 395 (September 25, 1999): 1–28. http://dx.doi.org/10.1017/s002211209900573x.

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The aerodynamic and acoustic properties of supersonic elliptic and circular jets are experimentally investigated. The jets are perfectly expanded with an exit Mach number of approximately 1.5 and are operated in the Reynolds number range of 25 000 to 50 000. The reduced Reynolds number facilitates the use of conventional hot-wire anemometry and a glow discharge excitation technique which preferentially excites the varicose or flapping modes in the jets. In order to simulate the high-velocity and low-density effects of heated jets, helium is mixed with the air jets. This allows the large-scale

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18

V., Sumesh, and Balachandran P. "Effect of Strut Geometry in Supersonic Mixing." International Journal of Engineering and Advanced Technology (IJEAT) 9, no. 6 (2020): 386–89. https://doi.org/10.35940/ijeat.F1529.089620.

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Effective mixing in a short mixing chamber is a major challenge in supersonic air breathing engines, especially the mixing between two high speed co-axial streams. The residence time is a major factor to get the two streams properly mixed. The selection of mixing method is crucial in the supersonic conditions. An experimental study has been performed on the supersonic mixing of air from strut injectors of various combinations in their trailing ramp angles with a free stream air of Mach number 2. Two different configurations of geometries, a plain geometry and a lobed geometry considered and fu

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19

Proskurov, Stan, Markus Lummer, Jan Werner Delfs, et al. "Installed Fan Noise Simulation of a Supersonic Business Aircraft." Aerospace 10, no. 9 (2023): 773. http://dx.doi.org/10.3390/aerospace10090773.

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Overcoming the problem of excessive engine noise at low altitudes is a formidable task on the way to developing a supersonic passenger aircraft. The focus of this paper is on the fan noise shielding during take-off, investigated as part of the DLR project ELTON SST (estimation of landing and take-off noise of supersonic transport) for an in-house aircraft design. The supersonic inlet is required to provide the proper quantity and uniformity of air to the engine over a wider range of flight conditions than the subsonic inlet. For passenger aircraft, the noise problem influences engine integrati

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20

Martínez-Ruiz, Daniel, César Huete, Pedro J. Martínez-Ferrer, and Daniel Mira. "Irregular self-similar configurations of shock-wave impingement on shear layers." Journal of Fluid Mechanics 872 (June 14, 2019): 889–927. http://dx.doi.org/10.1017/jfm.2019.336.

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An oblique shock impinging on a shear layer that separates two uniform supersonic streams, of Mach numbers $M_{1}$ and $M_{2}$, at an incident angle $\unicode[STIX]{x1D70E}_{i}$ can produce regular and irregular interactions with the interface. The region of existence of regular shock refractions with stable flow structures is delineated in the parametric space $(M_{1},M_{2},\unicode[STIX]{x1D70E}_{i})$ considering oblique-shock impingement on a supersonic vortex sheet of infinitesimal thickness. It is found that under supercritical conditions, the oblique shock fails to deflect both streams c

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21

Psota, Pavel, Gramoz Çubreli, Jindřich Hála, et al. "Characterization of Supersonic Compressible Fluid Flow Using High-Speed Interferometry." Sensors 21, no. 23 (2021): 8158. http://dx.doi.org/10.3390/s21238158.

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This paper presents a very effective interference technique for the sensing and researching of compressible fluid flow in a wind tunnel facility. The developed technique is very sensitive and accurate, yet easy to use under conditions typical for aerodynamic labs, and will be used for the nonintrusive investigation of flutter in blade cascades. The interferometer employs a high-speed camera, fiber optics, and available “of-the-shelf” optics and optomechanics. The construction of the interferometer together with the fiber optics ensures the high compactness and portability of the system. Moreov

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22

Lei, Zhong. "Flow Simulation of an Supersonic Transport Configuration at Low-Speed and High-Lift Conditions." Journal of Aircraft 45, no. 5 (2008): 1514–21. http://dx.doi.org/10.2514/1.33856.

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23

Theofanous, T. G., G. J. Li, and T. N. Dinh. "Aerobreakup in Rarefied Supersonic Gas Flows." Journal of Fluids Engineering 126, no. 4 (2004): 516–27. http://dx.doi.org/10.1115/1.1777234.

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We present new experimental results on the interfacial instabilities and breakup of Newtonian liquid drops suddenly exposed to rarefied, high-speed (Mach 3) air flows. The experimental approach allows for the first time detailed observation of interfacial phenomena and mixing throughout the breakup cycle over a wide range of Weber numbers. Key findings are that Rayleigh-Taylor instability alone is the active mechanism for freestream Weber numbers as low as 28 for low viscosity liquids and that stripping rather than piercing is the asymptotic regime as We→∞. This and other detailed visual evide

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Ferrero, Andrea. "Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed." Aerospace 7, no. 3 (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

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Liu, Qi, Juanmian Lei, Yong Yu, and Jintao Yin. "Aeroelastic Response of Spinning Projectiles with Large Slenderness Ratio at Supersonic Speed." Aerospace 10, no. 7 (2023): 646. http://dx.doi.org/10.3390/aerospace10070646.

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Obvious aeroelastic deformation occurs in spinning projectiles with large slenderness ratio, which seriously affects flight stability and maneuverability. This paper investigates the aeroelastic response of spinning projectiles with large slenderness ratio under supersonic speed. Based on a dynamic mesh method, an unsteady numerical simulation method is developed to study the aeroelasticity of spinning projectiles by coupling aerodynamics and structural dynamics. The numerical simulation method is well validated by the experimental results of AGARD 445.6 wing flutter. Then, the aeroelastic res

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26

Tsuchiya, Takao, and Masashi Kanamori. "Two-dimensional finite difference-time domain analysis of focus boom noise with velocity disturbance in the atmosphere." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 6 (2021): 589–97. http://dx.doi.org/10.3397/in-2021-1576.

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In this paper, two-dimensional linear sound wave analysis in the stratified atmosphere with temperature gradient and velocity disturbance is numerically applied to the analysis and prediction of focus boom noise. Focus boom occurs when a supersonic transport accelerates or ascent or descent maneuvers at supersonic speed. Its overpressure is typically more than three times greater than that of a cruise sonic boom. As a result, supersonic transports in future commercial operation are likely to face restrictions on their flight conditions. The compact-explicit finite difference-time domain method

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Zhou, Xiyue, Lifeng Wang, Jingnong Jiang, and Zhu Su. "Hypersonic Aeroelastic Response of Elastic Boundary Panel Based on a Modified Fourier Series Method." International Journal of Aerospace Engineering 2019 (March 24, 2019): 1–13. http://dx.doi.org/10.1155/2019/5164026.

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In this paper, an analytical method is proposed to directly obtain the aeroelastic time domain response of the elastic boundary panel. Based on a modified Fourier series method (MFSM), the vibration analysis of elastic boundary panels is carried out, after the dynamics equation of the panel is obtained. Then, the vibrational functions are combined with the supersonic piston theory to establish the aeroelastic equation. The aeroelastic time domain response of the panel is obtained to analyze the flutter speed of the panel more intuitively. Finally, the flutter speeds of panels with different le

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Yuansong, Zhang, Gong Zheng, Wang Zian, and Chen Yongliang. "Angular rate enhanced Overload Controller Design for Low-speed UAVs." Journal of Physics: Conference Series 2478, no. 10 (2023): 102008. http://dx.doi.org/10.1088/1742-6596/2478/10/102008.

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Abstract This paper investigates the overload controller for low-speed UAV maneuvering flight. Compared with high-speed and supersonic vehicles, low-speed UAVs are more sensitive to atmospheric disturbances during maneuvering and their signals are more sensitive. This paper combines UAV overload control theory and L1 adaptive theory to propose a longitudinal attitude control method based on overload control for low-speed UAVs. The method uses overload as the outer loop and pitch angle rate as the inner loop, and provides a reliable control scheme for maneuvering low-speed UAVs. Through simulat

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29

Doolabi, Mostafa Hadi, and Seyed Ali Tavakoli Sabour. "An experimental study of binary lateral jets on a standard model in subsonic, transonic, and supersonic cross-flows." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 9 (2018): 3141–52. http://dx.doi.org/10.1177/0954410018793783.

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There are numerous aerodynamic and nonaerodynamic methods to control flying devices, one of which is lateral jets, i.e. a high-speed method with convenient operation at low speeds or high altitudes. In this research, a new arrangement of lateral jets is examined by testing in a wind tunnel. The test is conducted on the Basic Finner model. In this design, the jets at the top and bottom of the model are arranged in pairs and parallel to each other. This combination, in addition to controlling pitch channel, provides the necessary conditions to control the roll channel. In this paper, pressure di

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Samal, Pradeep, Saravanan Selvakumar, Tanishq Kalet, Nisha Manure, and Nikhil Gangamkote. "Combustion Optimization of a Scramjet – A Numerical Flow Investigation Approach." International Journal of Research and Scientific Innovation XII, no. VII (2025): 16–23. https://doi.org/10.51244/ijrsi.2025.120700003.

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The Scramjet (Supersonic Combustion Ramjet) engine stands at the forefront of next-generation hypersonic propulsion systems, offering exceptional performance by sustaining combustion at supersonic speeds. However, achieving stable, efficient, and complete combustion within the extremely short residence time of high-speed airflow remains one of the most critical and challenging aspects in scramjet development. This study focuses on the optimization of combustion within scramjet engines to enhance overall efficiency, thrust output, and operational stability under hypersonic flight conditions. Th

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Gautam, Kaurab, Aatresh Karnam, Mohammad Saleem, and Ephraim Gutmark. "Effect of internal geometry on supersonic jet noise." Journal of the Acoustical Society of America 153, no. 3_supplement (2023): A283. http://dx.doi.org/10.1121/10.0018857.

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The current study discusses the experimental results of the effect of two types of nozzle internal geometries. The first configuration uses a common inlet that diverges the flow into two separate channels that feed twin rectangular nozzles, and the second configuration has the plug flow type system with twin rectangular nozzles drawing air from a common plenum. The nozzles are converging diverging type with design Mach number of 1.5. Flow conditions encompassing overexpanded, design, and underexpanded conditions are tested with acoustic data collected in the farfield and nearfield domains. Hig

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Usmonov, Botir Sh, Ismoil I. Safarov, and Muhsin Kh Teshaev. "Nonlinear flutter of the transient process of hereditarily deformable systems in supersonic flight mode." Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, no. 88 (2024): 124–37. http://dx.doi.org/10.17223/19988621/88/10.

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In this paper, the problem of nonlinear flutter of a transient process of a hereditarily deformable wing of an aircraft moving at supersonic speed is considered. The aim of the work is to study the flutter problem for plate elements of aircraft in a gas flow under loads caused by atmospheric turbulence. Aerodynamic effects are specified according to the linearized piston theory. Nonlinear wing oscillations are described by a system of nonlinear integro-differential equations. They are solved numerically by the method proposed by F. Badalov, which is based on the Bubnov–Galerkin method, finite

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Liu, Peng, Jian Li, Tuan Hua, and He Zhang. "Simulation Test of The Aerodynamic Environment of A Missile-Borne Pulsed Laser Forward Detection System at High Flight Speed." Photonics 10, no. 12 (2023): 1363. http://dx.doi.org/10.3390/photonics10121363.

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When a missile-borne pulsed laser forward detection system flies at supersonic speed, the laser beam will be distorted by the uneven outflow field, resulting in a significant reduction in ranging accuracy. In this paper, the impact of high flight speed on a pulsed laser detection system is studied. First, a new ray tracing method with adaptive step size adjustment is proposed, which greatly improves the computational efficiency. Second, the aerodynamic environment of a munition flying at high speed is simulated by an intermittent transonic and supersonic wind tunnel to obtain the schlieren dat

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Wennerstrom, A. J. "Some Experiments With a Supersonic Axial Compressor Stage." Journal of Turbomachinery 109, no. 3 (1987): 388–97. http://dx.doi.org/10.1115/1.3262118.

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Between 1970 and 1974, ten variants of a supersonic axial compressor stage were designed and tested. These included two rotor configurations, three rotor tip clearances, addition of boundary-layer control consisting of vortex generators on both the outer casing and the rotor, and the introduction of slots in the stator vanes. Design performance objectives were a stage total pressure ratio of 3.0 with an isentropic efficiency of 0.82 at a tip speed of 1600 ft/s (488 m/s). The first configuration passed only 70 percent of design flow at design speed, achieving a stage pressure ratio of 2.25 at a

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Zhou, Xuewen, Jian Xu, and Shuiyan Lv. "Verification of a ground-based method for simulating high-altitude, supersonic flight conditions." International Journal of Computational Materials Science and Engineering 07, no. 01n02 (2018): 1850005. http://dx.doi.org/10.1142/s2047684118500057.

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Ground-based methods for accurately representing high-altitude, high-speed flight conditions have been an important research topic in the aerospace field. Based on an analysis of the requirements for high-altitude supersonic flight tests, a ground-based test bed was designed combining Laval nozzle, which is often found in wind tunnels, with a rocket sled system. Sled tests were used to verify the performance of the test bed. The test results indicated that the test bed produced a uniform-flow field with a static pressure and density equivalent to atmospheric conditions at an altitude of 13–15[

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Torabi, Keivan, Hasan Afshari, and Farhad Haji Aboutalebi. "Vibration and flutter analyses of cantilever trapezoidal honeycomb sandwich plates." Journal of Sandwich Structures & Materials 21, no. 8 (2017): 2887–920. http://dx.doi.org/10.1177/1099636217728746.

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In this article, free flexural vibration and supersonic flutter analyses are studied for cantilevered trapezoidal plates composed of two homogeneous isotropic face sheets and an orthotropic honeycomb core. The plate is modeled based on the first-order shear deformation theory, and aerodynamic pressure of external flow with desired flow angle is estimated via the piston theory. For this goal, first applying the Hamilton's principle, the set of governing equations and boundary conditions are derived. Then, using a transformation of coordinates, the governing equations and boundary conditions are

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Boniface, V. Abraham, and A. Joseph Rijul Raj. "Fatigue Analysis of Forward Fuselage under Dynamic Conditions." Applied Mechanics and Materials 766-767 (June 2015): 1121–26. http://dx.doi.org/10.4028/www.scientific.net/amm.766-767.1121.

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The fuselage is one of the main component in aircraft to carry payload and passenger. The fuselage enclosed with high weight structure. The fuselage is hollow tube which holds all parts of the airplane together. The shape of the fuselage based on the mission of the aircraft. A supersonic fighter plane will be having streamlined fuselage to reduce the drag force enclosed with high speed flight and similarly the shape vary depend on the velocity. The design of fuselage is very complicated for designers because it takes about 60% of total weight of the aircraft and the contribution of fuselage to

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Kotani, Akira, Toshiharu Tanaka, and Atsushi Fujishiro. "Development of Shock-Wave-Powered Actuators for High Speed Positioning." International Journal of Automation Technology 5, no. 6 (2011): 786–92. http://dx.doi.org/10.20965/ijat.2011.p0786.

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A shock wave is a compressive wave which propagates at supersonic speed. A shock wave is generated by the emission of energy for a very short duration by high speed phenomena, such as explosions, discharges, collisions, high speed flights, etc. Shock tube experiments have played an important role in the field of high speed gas dynamics. A shock tube is usually divided by a diaphragm into a driver section and a driven section. Generally, the initial conditions of the driver and driven sections are high and low pressure, respectively. When the diaphragm breaks, a shock wave is generated in the d

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Kumakshev, S. A., and A. M. Shmatkov. "Constraints in the Problem of Calculating Optimal Trajectories for a Supersonic Non-Maneuverable Aircraft." Прикладная математика и механика 87, no. 4 (2023): 631–41. http://dx.doi.org/10.31857/s0032823523040070.

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The influence of phase and other constraints on the method of searching for the trajectories of the movement of a civil supersonic aircraft, which are optimal in terms of fuel consumption, is considered. Based on the solutions found by the dynamic programming method, taking into account numerous restrictions on flight altitude, pitch angle, normal high-speed overload, aircraft speed, engine thrust, etc., it is shown that almost all of these conditions can be ignored during the initial stage of calculations, since the optimal solution does not reach them. Therefore, one can first apply the maxi

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Saccone, Guido, and Marco Marini. "Chemical Kinetic Analysis of High-Pressure Hydrogen Ignition and Combustion toward Green Aviation." Aerospace 11, no. 2 (2024): 112. http://dx.doi.org/10.3390/aerospace11020112.

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In the framework of the “Multidisciplinary Optimization and Regulations for Low-boom and Environmentally Sustainable Supersonic aviation” project, pursued by a consortium of European government and academic institutions, coordinated by Politecnico di Torino under the European Commission Horizon 2020 financial support, the Italian Aerospace Research Centre is computationally investigating the high-pressure hydrogen/air kinetic combustion in the operative conditions typically encountered in supersonic aeronautic ramjet engines. This task is being carried out starting from the zero-dimensional an

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Gao, Yang, Zhi Chun Yang, and Jiang Xie. "Effect of Elevated Temperature on the Flutter Characteristics of FGM Panel." Advanced Materials Research 217-218 (March 2011): 107–12. http://dx.doi.org/10.4028/www.scientific.net/amr.217-218.107.

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This paper investigates the stability issues of functionally graded material (FGM) panels subjected simultaneously to both aerodynamic and thermal loads. Finite Element Method is employed to model the panel structures and the supersonic aerodynamics is calculated by the first-order piston theory. The critical buckling temperature elevation of the panels is at first predicted. The nonlinear static analysis of the panels is then implemented at certain interval of temperature elevation before buckling onset to obtain structural stiffness matrix. The flutter speed of the panels with updated stiffn

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Ölçmen, Semih M., Gary C. Cheng, Richard Branam, and Stanley E. Jones. "Minimum drag and heating 0.3-caliber projectile nose geometry." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 233, no. 6 (2018): 1990–2000. http://dx.doi.org/10.1177/0954406218779094.

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Understanding the performance of penetrators and aerodynamic bodies of revolution (missiles, rockets, aircraft noses, etc.) requires a close look at the drag and the heat transfer characteristics at a wide range of supersonic flight conditions. This research utilizes computational study and compares the aerothermal loads of supersonic flows around a new penetrator geometry, derived based on the optimization of the nose factor, to those of other common projectile shapes: conical, tangent-ogive, and power series nose geometries. The abundance of research on 0.3-caliber projectile made the choice

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Wang, Yuhui, Junhua Zhang, Zhaoyang Tian, and Lei Shi. "Freejet tests on a variable geometry supersonic inlet driven by shape memory alloys." Journal of Physics: Conference Series 3041, no. 1 (2025): 012007. https://doi.org/10.1088/1742-6596/3041/1/012007.

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Abstract Conventional variable geometry supersonic inlets have defects of high redundant mass, large size and poor control effect. A variable geometry inlet with the SMAs as the control element is experimentally studied in a high-speed wind tunnel. The control scheme for inlet shapes is proposed, and the operating characteristics of the variable geometry inlet under typical conditions have been examined. The deformation of the throat and forebody can ensure stable operation of the inlet in a wide flight Mach number domain.

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Chernyshov, M. V., and K. E. Savelova. "Ambiguity of solutions for shock wave structures formed in high-speed gas flows with a low adiabatic index." Aerospace Engineering and Technology 2, no. 1 (2024): 40–62. http://dx.doi.org/10.52467/2949-401x-2024-2-1-40-62.

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We considered branched shock-wave structures (triple configurations of shock waves) which forms in supersonic flows of perfect gas, mainly at high flow Mach numbers and low values of the adiabatic index. Ambiguity of the solution for triple configurations of steady shock waves formed at Mach reflection, including for configurations with a negative slope angle of the reflected shock, was studied analytically and numerically. The conditions for the coexistence of triple configurations which correspond to Mach reflection with other shock-wave structures are derived and graphically demonstrated.

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ChoHee Kim, Donghyun Gwan, and Minho Sena Nam. "Beyond the Atmosphere: The Revolution in Hypersonic Flight." Fusion of Multidisciplinary Research, An International Journal 2, no. 1 (2021): 152–63. https://doi.org/10.63995/idxp9691.

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Hypersonic flight, defined as traveling at speeds greater than Mach 5, represents a revolutionary frontier in aerospace technology, promising transformative impacts on both military and civilian aviation. This revolution is driven by advancements in materials science, propulsion systems, and aerodynamic design, enabling aircraft and missiles to operate efficiently in extreme conditions encountered at hypersonic speeds. Critical developments include scramjet (supersonic combustion ramjet) engines, which facilitate sustained hypersonic flight by efficiently mixing and combusting air at high velo

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He, L., and J. O. Ismael. "Computations of bladerow stall inception in transonic flows." Aeronautical Journal 103, no. 1025 (1999): 317–24. http://dx.doi.org/10.1017/s000192400006468x.

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Abstract A three-dimensional unsteady Navier-Stokes solver has been used to simulate stall inception in a single row ten passage segment of a transonic fan, the NASA rotor-67. At subsonic flow conditions, the 3D results illustrate a rotating stall inception with short scale part-span cells rotating at around 80% rotor speed, similar to that observed in some low speed experiments. However, at a supersonic relative inflow condition, the results show that an isolated blade row tends to stall in a one-dimensional breakdown pattern without first experiencing rotating stall. At near-stall conditions

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Wang, Chong, Yizhen Li, Mengqi Zheng, and Ke Wang. "Aerodynamic Characteristics of Supersonic Separator for Natural Gas Processing." Journal of Physics: Conference Series 2329, no. 1 (2022): 012045. http://dx.doi.org/10.1088/1742-6596/2329/1/012045.

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Abstract Natural gas is a key energy source to achieve the carbon peaking and carbon neutrality goals in China. Dehydration and de-hydrocarbon process is crucial for pipeline transportation of natural gas since water and hydrocarbons in the natural gas would condense to cause corrosion and freeze-blockage in the pipeline. The supersonic separator is innovative low-temperature separation equipment characterized by a simpler equipment structure and higher refrigeration efficiency than the traditional device. In this paper, the numerical analysis is employed to predict the performance of the supe

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Philishvili, E., B. M. Shergelashvili, S. Buitendag, J. Raes, S. Poedts, and M. L. Khodachenko. "Case study on the identification and classification of small-scale flow patterns in flaring active region." Astronomy & Astrophysics 645 (January 2021): A52. http://dx.doi.org/10.1051/0004-6361/202038895.

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Context. We propose a novel methodology to identity flows in the solar atmosphere and classify their velocities as either supersonic, subsonic, or sonic. Aims. The proposed methodology consists of three parts. First, an algorithm is applied to the Solar Dynamics Observatory (SDO) image data to locate and track flows, resulting in the trajectory of each flow over time. Thereafter, the differential emission measure inversion method is applied to six Atmospheric Imaging Assembly (AIA) channels along the trajectory of each flow in order to estimate its background temperature and sound speed. Final

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V. Starov, Alexey. "Determination of the limits of stable combustion at high supersonic flow velocities in a channel." Siberian Journal of Physics 3, no. 2 (2008): 47–60. http://dx.doi.org/10.54362/1818-7919-2008-3-2-47-60.

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In this paper, analysis of existing methods application of criterial description of ignition conditions and combustion break-out for summarizing of experimental results is carried out. Experimental results are obtained at investigations of hydrogen combustion in combustor with high supersonic speed of airflow. For these conditions selection of several criterions was substantiated and they have a good agreement with new experimental results. At the same time complexity of determination of experimental physical parameters, which are included in criterions, do not allow confidently to apply them

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Joo, W. G., and T. P. Hynes. "The Simulation of Turbomachinery Blade Rows in Asymmetric Flow Using Actuator Disks." Journal of Turbomachinery 119, no. 4 (1997): 723–32. http://dx.doi.org/10.1115/1.2841182.

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This paper describes the development of actuator disk models to simulate the asymmetric flow through high-speed low hub-to-tip ratio blade rows. The actuator disks represent boundaries between regions of the flow in which the flow field is solved by numerical computation. The appropriate boundary conditions and their numerical implementation are described, and particular attention is paid to the problem of simulating the effect of blade row blockage near choking conditions. Guidelines on choice of axial position of the disk are reported. In addition, semi-actuator disk models are briefly descr

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