In-Flight Nozzle Morphing Mechanism for a high speed Aircraft using a Retractable Nozzle Section

Navuday Sharma, Pritam Kumar Pratihari and Jayraj Inamdar

ABSTRACT Aircraft Engine Nozzles are designed to operate at a predetermined flight condition. Any variation of the aerodynamic environment, leads to reduction in the nozzle efficiency, which is the efficiency with which the potential energy is converted to the kinetic energy in a nozzle. To improve the aerodynamic performance of a convergent jet nozzle, it can be morphed into a convergent-divergent nozzle and vice versa, depending on the flight regimes, whether subsonic or supersonic respectively. Nozzle morphing can become a subject of extreme importance considering the aspect of nozzle efficiency. This paper presents a method for morphing the engine nozzle of an aircraft flying at supersonic speed. To demonstrate the nozzle efficiency, a CFD analysis is done on a convergent and convergent-divergentnozzle by simulating the flow using the software of GAMBIT for meshing and ANSYS FLUENT, for post-processing. An important aspect of extension and retraction of Retractable Divergent Nozzle Section, through hydraulic actuator system, is being proposed. This mechanism can be practically implemented. Though there are many structural and mechanical studies required for this mechanism, this paper mainly deals with the aerodynamic considerations of the generated idea. Keywords:Choke condition, Convergent nozzle, Convergent-Divergent nozzle, Critical nozzle pressure, Retractable Divergent Nozzle Section

Title:	In-Flight Nozzle Morphing Mechanism for a high speed Aircraft using a Retractable Nozzle Section
Author Name:	Navuday Sharma, Pritam Kumar Pratihari and Jayraj Inamdar
Abstract:	ABSTRACT Aircraft Engine Nozzles are designed to operate at a predetermined flight condition. Any variation of the aerodynamic environment, leads to reduction in the nozzle efficiency, which is the efficiency with which the potential energy is converted to the kinetic energy in a nozzle. To improve the aerodynamic performance of a convergent jet nozzle, it can be morphed into a convergent-divergent nozzle and vice versa, depending on the flight regimes, whether subsonic or supersonic respectively. Nozzle morphing can become a subject of extreme importance considering the aspect of nozzle efficiency. This paper presents a method for morphing the engine nozzle of an aircraft flying at supersonic speed. To demonstrate the nozzle efficiency, a CFD analysis is done on a convergent and convergent-divergentnozzle by simulating the flow using the software of GAMBIT for meshing and ANSYS FLUENT, for post-processing. An important aspect of extension and retraction of Retractable Divergent Nozzle Section, through hydraulic actuator system, is being proposed. This mechanism can be practically implemented. Though there are many structural and mechanical studies required for this mechanism, this paper mainly deals with the aerodynamic considerations of the generated idea. Keywords:Choke condition, Convergent nozzle, Convergent-Divergent nozzle, Critical nozzle pressure, Retractable Divergent Nozzle Section
Cite this article:	Navuday Sharma, Pritam Kumar Pratihari and Jayraj Inamdar , " In-Flight Nozzle Morphing Mechanism for a high speed Aircraft using a Retractable Nozzle Section " , International Journal of Application or Innovation in Engineering & Management (IJAIEM), Volume 4, Issue 1, January 2015 , pp. 163-167 , ISSN 2319 - 4847.
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