Abo Bibliothek: Guest

EFFECT OF VORTEX GENERATORS ON THE DIRECTION DIAGRAM OF ACOUSTIC EMISSION OF SUPERSONIC JETS

Volumen 45, Ausgabe 3-4, 2014, pp. 329-343
DOI: 10.1615/TsAGISciJ.2014011693
Get accessGet access

ABSTRAKT

The results of an experimental study on the influence of two types of vortex generators mounted at the exit of a convergent nozzle on the direction diagram of the acoustic emission of a supersonic under-expanded jet are reported. The vortex generators are chevrons or microjet injectors (six chevrons or six microjets). Both vortex generators are found to suppress the screech tone in jet noise. The effect of jet noise reduction using vortex generators is detected for Strouhal numbers lower than the critical value. For high Strouhal numbers, the noise intensity is found to increase. The value of the critical Strouhal number depends on the observation angle and vortex generator type. The use of a microjet generator leads to uniform reduction of jet noise in the entire range of observation angles. The presence of a chevron vortex generator leads to effective reduction of jet noise only for observation angles close to the jet exhaustion direction.

REFERENZIERT VON
  1. Gubanov D. A., Zapryagaev V. I., Kiselev N. P., Kundasev S. G., Aeroacoustic interaction in high-velocity jet with a thin obstacle, 2027, 2018. Crossref

  2. Zapryagaev Valery, Kiselev Nikolay, Gubanov Dmitry, Shock-Wave Structure of Supersonic Jet Flows, Aerospace, 5, 2, 2018. Crossref

  3. Gubanov D. A., Kundasev S. G., Trubitsyna L. P., Effect of artificial streamwise vortexes on characteristics of supersonic jet, HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2019): Proceedings of the XXVI Conference on High-Energy Processes in Condensed Matter, dedicated to the 150th anniversary of the birth of S.A. Chaplygin, 2125, 2019. Crossref

Neueste Ausgabe

KIRILL IVANOVICH SYPALO−50TH ANNIVERSARY NUMERICAL STUDY OF THE DISTURBANCES GENERATED BY MICROJETS IN A SUPERSONIC FLAT-PLATE BOUNDARY LAYER Andrei Valerievich Novikov, Alexander Vitalyevich Fedorov, Ivan Vladimirovich Egorov, Anton Olegovich Obraz, Nikolay Nikolaevich Semenov ANALYSIS OF THE MOVING DETONATION INTERACTION WITH TURBULENT BOUNDARY LAYERS IN A DUCT ON THE BASIS OF NUMERICAL SIMULATION Vladimir Anatolievich Sabelnikov, Vladimir Viktorovich Vlasenko, Sergey Sergeyevich Molev EXPERIMENTAL STUDY OF COUNTERFLOW BLOWING IN HIGH-SPEED FLOW THROUGH AN ASYMMETRIC SLOT IN THE LEADING EDGE OF A SHARP WEDGE Eduard Borisovich Vasilevskii, Ivan Valeryevich Ezhov, Pavel Vladimirovich Chuvakhov ASYMPTOTIC SOLUTIONS TO HYPERSONIC BOUNDARY LAYER EQUATIONS ON A FLAT WING WITH A POINT OF INFLECTION ON THE LEADING EDGE Georgiy Nikolaevich Dudin, Aleksey Vyacheslavovich Ledovskiy WAVE MODEL OF ORGANIZED STRUCTURES IN A TURBULENT BOUNDARY LAYER ON A PLATE WITH ZERO LONGITUDINAL PRESSURE GRADIENT Vladimir Alekseevich Zharov, Igor Ivanovich Lipatov, Rami Salah Saber Selim NUMERICAL SIMULATION OF THE FLOW AROUND LANDSCAPE FRAGMENTS AND SOLUTION VERIFICATION Viktor Viktorovich Vyshinsky, Koang T'in' Zoan POLYNOMIAL REPRESENTATION OF THERMODYNAMIC PROPERTIES OF COMBINED FUEL SYSTEMS IN RAMJET SIMULATION MODELS Timur Romanovich Zuev, Mikhail Semenovich Tararyshkin A MODEL TEST METHODOLOGY FOR THE INVESTIGATION OF AN ELASTICALLY SCALED MAIN ROTOR Maxim Andreyevich Ledyankin , Sergey Anatolyevich Mikhailov, Dmitry Valeryevich Nedel'ko, Timur Arturovich Agliullin INDEX, VOLUME 51, 2020
Digitales Portal Digitale Bibliothek eBooks Zeitschriften Referenzen und Berichte Forschungssammlungen Preise und Aborichtlinien Begell House Kontakt Language English 中文 Русский Português German French Spain