Volume 19, Issue 7 (July 2019)
Modares Mechanical Engineering 2019, 19(7): 1741-1750 |
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Babaeyan M, Hojaji M. Experimental investigation of the penetration effects of opposite dual protuberances on thrust vector of a supersonic C-D nozzle. Modares Mechanical Engineering 2019; 19 (7) :1741-1750
URL: http://mme.modares.ac.ir/article-15-21664-en.html
URL: http://mme.modares.ac.ir/article-15-21664-en.html
1- Mechanical Engineering Department, Engineering Faculty, Najafabad Branch, Islamic Azad University, Najafabad, Iran
2- Engineering Faculty, Najafabad Branch, Islamic Azad University, Najafabad, Iran
2- Engineering Faculty, Najafabad Branch, Islamic Azad University, Najafabad, Iran
Abstract: (2973 Views)
In this study, the effect of the use of dual protuberances as a thrust vector control method in a supersonic convergent-divergent nozzle with a Mach number of 2 is experimentally investigated. The nozzle total pressure in all experiments is considered constant. Air is the working fluid in these experiments. The used protuberances are two cylindrical elements that are placed in front of the flow in the divergent part of the nozzle. These protuberances are installed at 60% and 90% of the length of the nozzle divergent portion from the nozzle throat and are simultaneously applied in the main flow path. The protuberances are installed in opposite walls. Effect of changing the penetration ratio of the protuberances [H/D] on the thrust vector angle and the components of the thrust vector is obtained by measuring the forces acting on the nozzle. Also, the flow field was measured by a Schlieren system, as well as, the pressure variations on the nozzle walls were measured. The results show that the use of dual protuberances can have a significant effect on the angle of the thrust vector and increase the angle of the thrust vector up to 4.35 degrees in the implemented conditions of this study. Also, the results reveal that this method can reduce the axial component of thrust up to 5.5% in the worst case of implemented conditions.
Keywords: Thrust Vector Control, Convergent-Divergent Nozzle, Supersonic Flow, Protuberance, Experimental Aerodynamics
Article Type: Original Research |
Subject:
Experimental Fluid Mechanics
Received: 2018/06/2 | Accepted: 2018/12/29 | Published: 2018/07/1
Received: 2018/06/2 | Accepted: 2018/12/29 | Published: 2018/07/1
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