Zobrazeno 1 - 10
of 17
pro vyhledávání: '"Naren Shankar Radha Krishnan"'
Publikováno v:
Aircraft Engineering and Aerospace Technology. 95:878-889
Purpose In comparison to a nozzle with a larger/finite separation distance (Thanigaiarasu et al., 2019), a thin-lip nozzle (Srinivasarao et al., 2017) minimizes drag. Coaxial nozzles with thin lips are an appropriate tool for studying high subsonic j
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::b0a362db7f53264e29e92c1de2d29919
https://doi.org/10.1108/aeat-05-2022-0134
https://doi.org/10.1108/aeat-05-2022-0134
Publikováno v:
Journal of Aerospace Technology and Management, Vol 12, Iss 1 (2020)
Effect of Mach number on coflowing jet at lip thickness of 0.2 Dp, 1.0 Dp and 1.5 Dp (where Dp is primary nozzle exit diameter, 10 mm) at Mach numbers 1.0, 0.8 and 0.6 were studied experimentally. It was found that an increase in Mach number does not
Externí odkaz:
https://doaj.org/article/bfa7a69afbfd4015bacb90f4c5522f04
Publikováno v:
Energy Sources, Part A: Recovery, Utilization, and Environmental Effects. 44:8679-8693
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cdd7d265536f0955369183c40edd1c69
https://doi.org/10.1080/15567036.2022.2120572
https://doi.org/10.1080/15567036.2022.2120572
Publikováno v:
Advances in Materials and Processing Technologies. 8:4416-4439
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::56da1bd6f64d4e9c83f13b380bc65bdd
https://doi.org/10.1080/2374068x.2022.2076987
https://doi.org/10.1080/2374068x.2022.2076987
Publikováno v:
Aircraft Engineering and Aerospace Technology. 94:1614-1627
Purpose The purpose of this study is to analyse numerically and experimentally the effects of lip thickness (LT) and bypass ratio on co-flowing nozzle under subsonic and correctly expanded sonic jet decay at different Mach numbers. Design/methodology
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::431ef1337d147906909cf55e685e00ce
https://doi.org/10.1108/aeat-02-2021-0050
https://doi.org/10.1108/aeat-02-2021-0050
Autor:
Naren Shankar Radha Krishnan, Sathish Kumar Kumar, Vijayaraja Kengaiah, Senthilkumar Chidambaram, Ethirajan Rathakrishnan
Publikováno v:
International Journal of Turbo & Jet-Engines.
The characteristics of a sonic under-expanded coaxial jet with lip thickness 1.5D p (where D p is the exit diameter of primary jet equals 10 mm) with the primary jet operating at nozzle pressure ratio (NPR) of 3, 4 and 5. For NPR 3 operating primary
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::ac4f820089029d493153f1c6297cfd34
https://doi.org/10.1515/tjj-2022-0068
https://doi.org/10.1515/tjj-2022-0068
Hypersonic vehicles attain a speed five times more high-speed than the speed of sound, which is beyond Mach 5 and nearly equal to 6174km/h. Hypersonic flow has certain characteristics, essentially a reedy shock layer, formation of entropy layer, visc
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::93b1bd441524e6a3f52b3362a989b4fd
https://doi.org/10.4018/978-1-6684-4230-2.ch012
https://doi.org/10.4018/978-1-6684-4230-2.ch012
Autor:
Naren Shankar Radha Krishnan
Publikováno v:
Advances in Mechatronics and Mechanical Engineering ISBN: 9781668442302
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::fd435f48a1fbafb6f79866dc324c7831
https://doi.org/10.4018/978-1-6684-4230-2
https://doi.org/10.4018/978-1-6684-4230-2
Publikováno v:
International Journal for Simulation and Multidisciplinary Design Optimization. 14:3
Aerofoil noise as self-noise is detrimental to system performance, in this paper NACA 0012 optimization parameters are presented for reduction in noise. Designing an aerofoil with little noise is a fundamental objective of designing an aircraft that
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::36c42f5c59deeb6226f52545776ab36b
https://doi.org/10.1051/smdo/2023002
https://doi.org/10.1051/smdo/2023002
Publikováno v:
Journal of Aerospace Technology and Management v.12 2020
Journal of Aerospace Technology and Management
Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron:DCTA
Journal of Aerospace Technology and Management, Vol 12, Iss 1, Pp 2520-2520 (2020)
Journal of Aerospace Technology and Management
Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron:DCTA
Journal of Aerospace Technology and Management, Vol 12, Iss 1, Pp 2520-2520 (2020)
Effect of Mach number on coflowing jet at lip thickness of 0.2 Dp, 1.0 Dp and 1.5 Dp (where Dp is primary nozzle exit diameter, 10 mm) at Mach numbers 1.0, 0.8 and 0.6 were studied experimentally. It was found that an increase in Mach number does not
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::cd34961dc602cecf14a53f3db3890eb6
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462020000100324
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462020000100324