Numerical Simulation of Supersonic Jet Impingement on Inclined Plate

2013 ◽  
Vol 63 (4) ◽  
pp. 355-362 ◽  
Author(s):  
Malsur Dharavath ◽  
Debasis Chakraborty
Keyword(s):  
Numerical Simulation ◽  
Supersonic Jet ◽  
Jet Impingement ◽  
Inclined Plate

scholarly journals Numerical Simulation and Experiment of Supersonic Jet Impingement on a Plate.

1998 ◽  
Vol 46 (536) ◽  
pp. 485-496 ◽  
Author(s):  
Nobuyuki TSUBOI ◽  
A. Koichi HAYASHI ◽  
Toshitaka FUJIWARA ◽  
Kazuo ARASHI ◽  
Masaru KODAMA
Keyword(s):  
Numerical Simulation ◽  
Supersonic Jet ◽  
Jet Impingement ◽  
Simulation And Experiment

Numerical Simulation of a Supersonic Jet Impingement on a Ground

1991 ◽  
Author(s):  
Nobuyuki Tsuboi ◽  
A. Koichi Hayashi ◽  
Toshi Fujiwara ◽  
Kazuo Arashi ◽  
Masaru Kodama
Keyword(s):  
Numerical Simulation ◽  
Supersonic Jet ◽  
Jet Impingement

Acoustic Phenomena from Correctly Expanded Supersonic Jet Impinging on Inclined Plate

AIAA Journal ◽  
2015 ◽  
Vol 53 (7) ◽  
pp. 2061-2067 ◽  
Author(s):  
Masahito Akamine ◽  
Yuta Nakanishi ◽  
Koji Okamoto ◽  
Susumu Teramoto ◽  
Takeo Okunuki ◽  
...  
Keyword(s):  
Supersonic Jet ◽  
Inclined Plate

Numerical Simulation of Supersonic Jet Control by Tabs with Slanted Perforation

2019 ◽  
Vol 0 (0) ◽  
Author(s):  
G. Ezhilmaran ◽  
Suresh Chandra Khandai ◽  
Yogesh Kumar Sinha ◽  
S. Thanigaiarasu
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Near Field ◽  
Pressure Ratio ◽  
Supersonic Jet ◽  
Pressure Gradients ◽  
Nozzle Pressure Ratio ◽  
Nozzle Pressure ◽  
Jet Control ◽  
Different Diameters

Abstract This paper presents the numerical simulation of Mach 1.5 supersonic jet with perforated tabs. The jet with straight perforation tab was compared with jets having slanted perforated tabs of different diameters. The perforation angles were kept as 0° and 10° with respect to the axis of the nozzle. The blockage areas of the tabs were 4.9 %, 4.9 % and 2.4 % for straight perforation, 10° slanted perforation ( {{{\Phi }}_{\ }} = 1.3 mm) and 10° slanted perforation ( {{{\Phi }}_{\ }} = 1.65 mm) respectively. The 3-D numerical simulations were carried out using the software. The mixing enhancements caused by these tabs were studied in the presence of adverse and favourable pressure gradients, corresponding to nozzle pressure ratio (NPR) of 3, 3.7 and 5. For Mach number 1.5 jet, NPR 3 corresponds to 18.92 % adverse pressure gradients and NPR 5 corresponds to 35.13 % favourable pressure gradients. The centerline Mach number of the jet with slanted perforations is found to decay at a faster rate than uncontrolled nozzle and jet with straight perforation tab. Mach number plots were obtained at both near-field and far field downstream locations. There is 25 % and 65 % reduction in jet core length were observed for the 0° and 10° perforated tabs respectively in comparison to uncontrolled jet.

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