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Your search keyword '"Supersonic wind tunnel"' showing total 6 results
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6 results on '"Supersonic wind tunnel"'

1. Improved Analytical/Statistical Modelling of the Shock Wave-Laminar Boundary Layer Around a Thin Airfoil: Standard Atmosphere Case

Author

Eddegdag, Nasser, El-Aajine, Omar, Naamane, Aze-eddine, Radouani, Mohammed, Chaari, Fakher, Series Editor, Gherardini, Francesco, Series Editor, Ivanov, Vitalii, Series Editor, Cavas-Martínez, Francisco, Editorial Board Member, di Mare, Francesca, Editorial Board Member, Haddar, Mohamed, Editorial Board Member, Kwon, Young W., Editorial Board Member, Trojanowska, Justyna, Editorial Board Member, Xu, Jinyang, Editorial Board Member, Azrar, Lahcen, editor, Jalid, Abdelilah, editor, Lamouri, Samir, editor, Siadat, Ali, editor, and Taha Janan, Mourad, editor

Published
2023
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2. Numerical Investigation of Blockage of Scramjet Strut Injector Model in a Supersonic Wind Tunnel

Author

Sekar, Anbarasan, Chakraborty, Mayukhmali, Vaidyanathan, Aravind, Cavas-Martínez, Francisco, Editorial Board Member, Chaari, Fakher, Series Editor, di Mare, Francesca, Editorial Board Member, Gherardini, Francesco, Series Editor, Haddar, Mohamed, Editorial Board Member, Ivanov, Vitalii, Series Editor, Kwon, Young W., Editorial Board Member, Trojanowska, Justyna, Editorial Board Member, Sivaramakrishna, Gullapalli, editor, Kishore Kumar, S., editor, and Raghunandan, B. N., editor

Published
2023
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3. Development of a fast-stabilized fuel injection system using a solenoid actuator.

Author

Jeong, Junho, Kim, Keunyeong, Jang, Byungkook, and Park, Gisu

Subjects
*FUEL systems, *VALVES, *FUEL pumps, *FLOW visualization, *SUPERSONIC flow, *WIND tunnels, *ACTUATORS, *SOLENOIDS
Abstract

A new fuel injection system with a solenoid actuator was developed to reduce jet stabilization times and was compared to a conventional fuel injection system using a fast-acting valve. The jet stabilization time was examined from free-jet images obtained using a flow visualization technique. Using a supersonic wind tunnel, the jet establishment image and trajectory for supersonic flows were obtained. The jet stabilization times were obtained at fuel tank pressures of 500, 700, and 900 kPa and injection orifice diameters of 1 and 2 mm. For all cases, the jets were stabilized at 4–12 ms, which was shorter than the stabilization time (approximately 300 ms) of the conventional system. The injection pressure measurements and jet trajectory comparison showed that the new system could inject fuel at the target pressure more effectively than the conventional fuel system. [ABSTRACT FROM AUTHOR]

Published
2023
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4. UNS3D Near-Field Predictions for the Third AIAA Sonic Boom Prediction Workshop

Author

Jackson Kassing, Forrest L. Carpenter, and Paul G. A. Cizmas

Subjects
Supersonic wind tunnel, Turbulence, Shear stress, Aerospace Engineering, Near and far field, Mechanics, Geology, Sonic boom
Abstract

This paper presents the results of turbulent flow simulations prepared for the Third AIAA Sonic Boom Prediction Workshop. Solutions were prepared for two geometries that exhibited shock–plume inter...

Published
2022
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5. DLR TAU Near-Field Simulations for the Third AIAA Sonic Boom Prediction Workshop

Author

Kirz, Jochen

Subjects
Sonic Boom C608 Biconvex Validation Verfication Shock-Plume Interaction, Supersonic wind tunnel, Computer simulation, business.industry, Angle of attack, Aerospace Engineering, Near and far field, Sonic boom, Mass flow rate, Supersonic speed, Aerospace engineering, business, Reynolds-averaged Navier–Stokes equations, Geology
Abstract

The accurate prediction of the sonic boom is essential for the development of a future low-boom supersonic aircraft. In this paper, the best practice for predicting near-field pressure signatures w...

Published
2022
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6. Velocity measurements in a supersonic wind tunnel with a novel calibration-free seedless velocimetry utilizing laser-induced shockwaves and a double-line probe system

Author

Taekeun Yoon, Hyungrok Do, Juhyun Bae, Hosung Byun, Sanghoon Lee, Campbell D. Carter, and Inyoung Yang

Subjects
Fluid Flow and Transfer Processes, Physics, Supersonic wind tunnel, business.industry, Mechanical Engineering, Velocimetry, Condensed Matter Physics, Laser, law.invention, Physics::Fluid Dynamics, Optics, Flow velocity, law, Potential flow, business, Choked flow, Beam (structure), Wind tunnel
Abstract

A novel calibration-free seedless velocimetry technique utilizing a shockwave generated by a laser-induced plasma (LIP) is proposed and used for measuring velocity profile in a supersonic flow. A nanosecond laser pulse of 532-nm wavelength is focused in the test section of a supersonic wind tunnel to generate the LIP that emanates a shockwave. A continuous-wave laser beam of 658-nm wavelength traverses the region adjacent to the LIP twice between a knife-edge mirror and a retroreflecting mirror. The probe beam is monitored by a fast photodiode after the second reflection from the knife-edge mirror, to record the arrival of the LIP shockwaves at the two probe beam locations; the laser beam deflects when the shockwave reaches the beam, and this deflection is registered on the photodiode signal read by an oscilloscope. It is shown that the shockwave-arrival time is highly sensitive to the convection speed of the flow that carries the shockwave. An empirical point-explosion blast model, determining time-dependent shockwave location, is used to calculate the average convection velocity between the LIP and the farthest probe beam 4.5 mm from the LIP with a precision of better than 8 m/s (1.5%). The empirical model contains two coefficients, a shockwave-propagation coefficient and the flow velocity, which are determined by the shockwave-arrival times and the locations of the two probe beams relative to the LIP. The LIP is positioned along a span-wise direction of the supersonic wind tunnel to measure the velocity profile; the probe beams are parallel with the spanwise direction. Uniform flow velocity is found within the core-flow of the wind tunnel, which well agrees with the velocity estimated by the pressure and temperature measured in the tunnel.

Published
2022
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