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A study of particle growth in a rocket nozzle. [PDF]

AIAA Journal, 1966
The purpose of this study was to investigate condensed-phase particle growth in a rocket nozzle by particle collision and coalescence. An analysis is developed wherein it is assumed that the more rapidly moving smaller particles collide and coalesce with the larger ones, forming even larger particles and increasing the mass-median particle diameter ...
Paul G. Willoughby, Clayton T. Crowe
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Flow phenomena in advanced rocket nozzles - The plug nozzle

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
In recent years, plug nozzles have gained a renewed interest in space business. In principle, this nozzle concept offers a continuous altitude adaptation up to its design pressure ratio. But, the flow adaptation achieved with this advanced rocket nozzle concept induces shocks and expansion waves resulting in exit profiles far away from idealized one ...
Hagemann, G., Immich, H., Terhardt, M.
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Numerical Simulation of Rocket Nozzle

Advanced Materials Research, 2014
The vent or opening is called nozzle. The objectives are to measure the flow rates and pressure distributions within the converging and diverging nozzle under different exit and inlet pressure ratios. Analytic results will be used to contrast the measurements for the pressure and normal shock locations.
Srinivasa Rao Potti, G. Srinivas
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Shock-Generated Vortices in Rocket Nozzles

43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005
During the engine startup and shutdown of space launchers the nozzles operate in overexpanded regime, and flow separations in the divergent section may take place; their asymmetric character can yield side loads on the nozzle wall, with consequent major structural problems.
NASUTI, Francesco, ONOFRI, Marcello, E. PIETROPAOLI   +2 more
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Flow Characteristics of Overexpanded Rocket Nozzles

International Journal of Aerospace Innovations, 2010
The current paper discusses the exhaust flow features and the various unsteady flow separation characteristics in subscale overexpanded nozzles that lead to generation of side-loads. While a DiMR type of Mach reflection features in the exhaust of a truncated ideal contour nozzle an InMR occurs in a thrust optimized parabolic nozzle.
Haidn, O. J., Verma, S. B.
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Flow Separation in Rocket Nozzles - An Overview

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013
The paper includes a literature overview on the history of separated rocket nozzle flow research as well as a data base on flow separation in convergent-divergent nozzles.
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FREE VIBRATIONS OF ROCKET NOZZLES

Symposium on Structural Dynamics and Aeroelasticity, 1965
Fig. 4 Flowfield of a parallel flow nozzle exhausting normal to a concave surface in a vacuum (h/re = 10, RJh = 1.1, R = 60 ft/°R, Me = 4.0, 6e = 0°, 7 = 1.2, Bs = 1.0). 2 Roberts, L., "The action of a hypersonic jet on a dust layer/' IAS Paper 63-50 (1963). 3 Van Dyke, M. and Gordon, H. D., "Supersonic flow past a family of blunt axisymmetric bodies,"
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Erosion in rocket motor nozzles

Wear, 1977
Abstract Examination of the nozzle assemblies of solid propellant rocket motors has shown that erosion of molybdenum inserts occurs by three distinct processes. Wear was initiated by the physical erosion of the steel nozzle body due to particles in the gas stream.
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Transient surface temperatures in rocket nozzles

Journal of Spacecraft and Rockets, 1964
c = specific heat of solid, Btu/lb-°F d = half-thickness of node, in. erf = error function h = heat-transfer coefficient, convective plus radiant heating, Btu/sec-in.-°F = thermal conductivity of solid, Btu/sec-in.-°F/in. Mn = eigen values of MntsinMn = NBI NBI = Biot number, NBI = hd/k NFO = Fourier modulus, NFO = &0/8 n = number of eigenvalues T ...
G. T. Y. Chao, J. A. Jacobsen, J. T. Anderson   +2 more
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Contoured Rocket Nozzles

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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