Range of “complete” instability of flat flames propagating downward in the acoustic field in combustion tube: Lewis number effect

2020 ◽  
Vol 216 ◽  
pp. 326-337 ◽  
Author(s):  
Ajit K. Dubey ◽  
Yoichiro Koyama ◽  
Sung Hwan Yoon ◽  
Nozomu Hashimoto ◽  
Osamu Fujita
Keyword(s):  
Acoustic Field ◽  
Lewis Number ◽  
Combustion Tube

LEWIS NUMBER AND VAPORIZATION EFFECTS IN SPRAY DIFFUSION FLAMES

1993 ◽  
Vol 3 (4) ◽  
pp. 437-462 ◽  
Author(s):  
J. Barry Greenberg ◽  
I. Shpilberg
Keyword(s):  
Diffusion Flames ◽  
Lewis Number

APPLICATION OF THE HIGH-RESOLUTION RANS/ILES TECHNOLOGY FOR FLOW SIMULATION AND THE NEARBY ACOUSTIC FIELD OF NEAR-WALL JETS AND MIXING LAYERS

2016 ◽  
Vol 47 (2) ◽  
pp. 159-183 ◽  
Author(s):  
Leonid Aleksandrovich Bendersky ◽  
Dmitriy Aleksandrovich Lyubimov ◽  
Irina Vasilevna Potekhina ◽  
Alena Eduardovna Fedorenko
Keyword(s):  
High Resolution ◽  
Acoustic Field ◽  
Flow Simulation ◽  
Mixing Layers ◽  
Wall Jets ◽  
Near Wall

CALCULATION OF THE INTEGRAL NOISE LEVEL AT A FIELD POINT OF A FREE SUPERSONIC JET OF A ROCKET ENGINE

Akustika ◽  
2020 ◽  
Vol 36 (36) ◽  
pp. 22-24
Author(s):  
Anatoly Kochergin ◽  
Valeeva Ksenia
Keyword(s):  
Acoustic Field ◽  
Noise Level ◽  
Rocket Engine ◽  
Supersonic Jet ◽  
Noise Sources ◽  
Field Point

The paper considers an acoustic field created by a supersonic jet (CES) of a rocket engine freely flowing into flooded space. The acoustic field was presented in the form of a diagram of noise isobars, from which it can be seen that the acoustic field is formed by two effective noise sources: the nearest one, lying at a distance of 5-10 calibers from the nozzle cut and the far one, lying at a distance of 15-30 calibers from the nozzle cut.

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