Effects of Key Inlet Design Parameters on the Performance of Supplementary Combustion Nozzle [PDF]
Journal of Applied Fluid MechanicsSolid rocket motors (SRMs) have limited propulsion performance due to their short fuel combustion duration and low specific impulse. The supplementary combustion nozzle (SCN) injects air into the nozzle expansion section to promote secondary combustion ...
W. Lei, Y. Li, Q. Liu, Z. Zhou
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Design and fabrication requirements for low noise supersonic/hypersonic wind tunnels [PDF]
A schematic diagram of the new proposed Supersonic Low Disturbance Tunnel (SLDT) is shown. Large width two dimensional rapid expansion nozzles guarantee wide quiet test cores that are well suited for testing models at large angle of attack and for swept ...
Beckwith, Ivan E. +2 more
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Numerical study of acoustic oscillations and combustion instabilities in solid propellant rocket [PDF]
, 1997 A numerical analysis of unsteady motions in solid rocket motors has been conducted. A fully coupled implicit scheme based on a dual time-stepping integration algorithm has been adopted to solve the governing equations and associated boundary conditions.
Culick, F. E. C., Roh, T. S.
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Influence of jet blast deflector with fold angle on supersonic jet flow
Zhongguo Jianchuan Yanjiu, 2019 [Objectives] In order to study the performance of Jet Blast Deflector(JBD)and its influence on the surrounding flow field during the takeoff or ground testing of the fighter,this paper studies the typical axisymmetric convergent-divergent nozzle and the ...
GUO Kai, WANG Qiang
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Bibliography on aerodynamics of airframe/engine integration of high-speed turbine-powered aircraft, volume 1 [PDF]
This bibliography was developed as a first step in the preparation of a monograph on the subject of the aerodynamics of airframe/engine integration of high speed turbine powered aircraft.
Nichols, M. R.
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Archives of Acoustics, 2016 The behaviour of screeching jets exhausting from an axisymmetric con-vergent-divergent nozzle was studied. The nozzle had a 2.9 mm throat diameter and a. 1.95 theoretical exit Mach number.
Giovanni Maria CARLOMAGNO +2 more
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Effects of Erosive Burning on Solid Rocket Motor Internal Ballistics [PDF]
فصلنامه علوم و فناوری فضایی, 2012 In this study, solid rocket motor internal ballistic, has been investigated. Flow field consists of internal grain space and converging-diverging nozzle. Axisymmetric, compressible and transient Euler equations have been considered as governing equations
E. Rezaeian Parsa, S. M. Mirsajedi
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Computer code for the prediction of nozzle admittance [PDF]
A procedure which can accurately characterize injector designs for large thrust (0.5 to 1.5 million pounds), high pressure (500 to 3000 psia) LOX/hydrocarbon engines is currently under development.
Nguyen, Thong V.
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Impact of Lens Angle and Nozzle Geometry on Aerodynamic Focusing: A Numerical Study
AtmosphereStraight-edge thin plate orifices (90° half-angle) are used as the focusing elements in most aerodynamic lenses. They are simple to fabricate and have fewer boundary-layer effects as compared to other geometries, such as capillaries and converging and ...
Apolo Vannavong +3 more
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Streamwise vorticity generation and mixing enhancement in free jets by delta-tabs [PDF]
The effect of triangular tabs, placed at the nozzle exit, on the evolution of free jets is investigated. The effect, a large distortion of the jet cross section and a resultant increase in mixing downstream, has been inferred before to be due to a pair ...
Zaman, K. B. M. Q.
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