Non-equilibrium dissociating nitrogen flow over spheres and circular cylinders [PDF]
, 1972 Theoretical results based on the methods of Freeman and Garr & Marrone show that the stand-off distance and flow pattern of non-equilibrium dissociating flow of nitrogen over the front part of a blunt body can be correlated in terms of a single reaction ...
Hornung, H. G.
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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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Divergence thrust loss calculations for convergent-divergent nozzles: Extensions to the classical case [PDF]
The analytical derivations of the non-axial thrust divergence losses for convergent-divergent nozzles are described as well as how these calculations are embodied in the Navy/NASA engine computer program.
Berton, Jeffrey J.
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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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Experimental and analytical investigation of axisymmetric supersonic cruise nozzle geometry at Mach numbers from 0.60 to 1.30 [PDF]
Quantitative pressure and force data for five axisymmetric boattail nozzle configurations were examined. These configurations simulate the variable-geometry feature of a single nozzle design operating over a range of engine operating conditions.
Carson, G. T., Jr., Lee, E. E., Jr.
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Static performance of an axisymmetric nozzle with post-exit vanes for multiaxis thrust vectoring [PDF]
An investigation was conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to determine the flow-turning capability and the nozzle internal performance of an axisymmetric convergent-divergent nozzle with post-exit vanes installed ...
Berrier, Bobby L., Mason, Mary L.
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Impinging Jet Resonant Modes at Mach 1.5 [PDF]
, 2013 High speed impinging jets have been the focus of several studies owing to their practical application and resonance dominated flow-field. The current study focuses on the identification and visualization of the resonant modes at certain critical ...
Alvi, Farrukh, Davis, Timothy
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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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