Results 261 to 270 of about 14,137 (299)
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1959
A method of designing rocket nozzle wall contours to yield optimum thrust is presented. The rocket exhaust gases are treated under the assumption of isentropic, adiabatic and frictionless flow. Nozzle length and ambient pressure appear as governing restrictions under which the thrust is maximized.
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A method of designing rocket nozzle wall contours to yield optimum thrust is presented. The rocket exhaust gases are treated under the assumption of isentropic, adiabatic and frictionless flow. Nozzle length and ambient pressure appear as governing restrictions under which the thrust is maximized.
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Investigation of the infrared characteristics of the rocket nozzle
IEEE Aerospace and Electronic Systems Magazine, 2009Investigation of the infrared characteristics of a rocket nozzle is very important for the study of infrared initiating technology. The Narrow-Band Zone model is developed for that purpose. The spectral transmission and absorption factors are introduced, and the equations between radiative heat flux and the temperature of waill surfaces and gas are ...
Guobiao Cai, Xiaoying Zhang
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Chemical Kinetics and Rocket Nozzle Design
Journal of the American Rocket Society, 1951Abstract : The effect of chemical kinetics on rocket nozzle design was investigated for the particular case of hydrogen gas flowing adiabatically through a typical rocket nozzle having a chamber-to-throat-area ratio of 2 to 1. For comparative purposes the following types of flow were considered: (a) constant composition (frozen equilibrium), (b ...
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High-Performance Rocket Nozzle Concept
Journal of Propulsion and Power, 2010An innovative technical solution that overcomes the limitation induced by flow separation phenomena and allows increasing the vacuum-specific impulse of a main stage rocket engine is presented. After reviewing the open technical literature on flow separation and advance nozzles design, the newly proposed concept is extensively presented.
Luca Boccaletto, Jean-Paul Dussauge
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Recent Developments in Rocket Nozzle Configurations
ARS Journal, 1961T THRUST of a rocket engine is primarily dependent upon the momentum imparted to the products of combustion by discharging them through an exhaust nozzle. During their passage through the nozzle, the exhaust gases are continuously accelerated from low subsonic velocities to high supersonic velocities at the nozzle exit. For the purpose of understanding
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Performance of the aerobell extendible rocket nozzle
Journal of Spacecraft and Rockets, 1969Aerobell extendible nozzle rocket engine design and performance, cold flow and simulated hot flow test ...
G. A. Hosack, R. R. Stromsta
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Flow separation and side-loads in rocket nozzles
35th Joint Propulsion Conference and Exhibit, 1999Flow separation in nozzles of rocket engines is undesired because it can lead to dangerous lateral forces, which might damage the nozzle. The origin of side-loads is not fully clear, although different possible origins were identified in the past. Meanwhile, it seems to be clear that in thrust-optimized or parabolic nozzles, a major side-load is due to
Frey, M., Hagemann, G.
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A Philosophy for Improved Rocket Nozzle Design
Journal of Jet Propulsion, 1957Th i s pape r p r e s e n t s a t h r e e d i m e n s i o n a l ana lys i s of superson ic c o n t o u r e d rocke t nozzles . T h e s t u d y was u n d e r t a k e n i n o rde r t o ar r ive a t t h e des ign of s h o r t , axially s y m m e t r i c nozzles hav ing axially d i rec ted e x h a u s t a n d e i the r , or b o t h , improved p e r f o r m
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Reacting Flow Simulation of Rocket Nozzles
2016Reacting flow simulation of high area ratio rocket nozzles is done using an indigenously developed Point Implicit Unstructured Finite Volume Solver. A numerical solution procedure to solve turbulent-reacting nozzle flow field is developed, which is based on the implicit treatment of chemical source terms by preconditioning and then explicitly solved ...
T. Jayachandran +3 more
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Advanced rocket engine nozzles [PDF]
32nd Joint Propulsion Conference and Exhibit, 1996 N. Ponomarev, G. Dumnov, G. Nikulin
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