Results 231 to 240 of about 13,247 (287)
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34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
An analysis is presented to simulate the turbulent compressible flow in converging diverging nozzles using a time-marching finite difference scheme of MacCormack. The Navier-Stokes equations governing the physical domain are transformed to a rectangular computational domain and the resulting equations are cast into finite difference form. The effect of
V. Jones, K. Shukla
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An analysis is presented to simulate the turbulent compressible flow in converging diverging nozzles using a time-marching finite difference scheme of MacCormack. The Navier-Stokes equations governing the physical domain are transformed to a rectangular computational domain and the resulting equations are cast into finite difference form. The effect of
V. Jones, K. Shukla
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Numerical Simulation of Rocket Nozzle
Advanced Materials Research, 2014The 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.
G. Srinivas, Srinivasa Rao Potti
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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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Shock-Generated Vortices in Rocket Nozzles
43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005During 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 +2 more
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Gas Deployed Skirt for rocket motor nozzles
13th Propulsion Conference, 1977The gas-deployed skirt (CDS) is a metal nozzle extension that is folded radially inward and packaged entirely within the cavity of a rocket motor nozzle. The skirt is deployed by low-pressure motor ignition gases and then stabilized in the open position by the internal pressure of fully developed nozzle exhaust gas flow.
Lee Carey, Geoffrey Nixon
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Flow Characteristics of Overexpanded Rocket Nozzles
International Journal of Aerospace Innovations, 2010The 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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Solid rocket nozzle design summary
4th Propulsion Joint Specialist Conference, 1968Solid rocket nozzle design, discussing configuration, material selection and aerodynamic, thermodynamic and stress ...
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Transient surface temperatures in rocket nozzles
Journal of Spacecraft and Rockets, 1964c = 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 ...
GEORGE T. Y. CHAO +2 more
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Erosion in rocket motor nozzles
Wear, 1977Abstract 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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Flow Separation in Rocket Nozzles - An Overview
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013The 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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