Results 181 to 190 of about 18,103 (226)

Transonic flow in plane and axisymmetric nozzles

1966
The solution of the transonic flow problem in the throat of a convergent-divergent nozzle in which the fluid is continuously accelerated from subsonic to supersonic velocities has been studied by many authors. In particular a first order linearized solution was first reported by Sauer [1].
R. Hetherington, M. E. Silvester
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Design of axisymmetric contoured nozzles for laminar hypersonic flow

3rd Aerodynamics Testing Conference, 1968
A method for design of axisymmetric nozzles for high-speed, low-density flows is described, with emphasis on treatment of very thick laminar boundary layers. An inviscid "expansion core" of flow is calculated by the method of characteristics, and the displacement boundarylayer thickness distribution calculated by the method of Cohen and Reshotko, with ...
J. LEITH POTTER, WILLIAM H. CARDEN
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Radiating hydrogen flow in axisymmetric nozzles

Fluid Dynamics, 1967
A considerable number of studies published in recent years have been devoted to the study of gas in channels and pipes. In view of the complexity of the question and the lack of analytic techniques, individual aspects of the problem are generally considered.
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Discharge coefficients for axisymmetric supersonic nozzles

37th Aerospace Sciences Meeting and Exhibit, 1999
Computational Fluid Dynamics (CFD) analysis was used to compute effective nozzle discharge coefficients for subscale sharp-edged converging/diverging nozzles, with a variety of convergence half-angles, motor operating conditions, and two propellants with different ballistics. Convergence half-angles ranged from 0 to 80 deg.
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Aerodynamic design of axisymmetric hypersonic wind tunnel nozzles

3rd Flight Test, Simulation, and Support Conference, 1969
A unified approach to nozzle design is presented in which an inviscid contour is first determined and then corrected to account for the growth of a turbulent boundary layer along the contour. The inviscid contour is obtained by the axisymmetric method of characteristi cs from a prescribed distribution of velocity along the nozzle axis.
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Analysis of an axisymmetric two-stream nozzle plume

15th Applied Aerodynamics Conference, 1997
The issue of noise generated from aircraft jet engine exhaust has become an important consideration for current and future engines. The ability to predict the acoustic characteristics of an exhaust depends on the accurate prediction of the nozzle plume and associated turbulence quantities using computational fluid dynamics (CFD) methods.
C. Smith, Nathan Snyder, Baily Vittal, C. Smith, Nathan Snyder, Baily Vittal   +5 more
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Advanced Mach 3.5 Axisymmetric Quiet Nozzle

21st Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1990
To advance boundary-layer stability and transition research and to ultimately provide reliable predictions of transition for supersonic flight vehicles, a wind tunnel is required with very low stream disturbance levels comparable to free flight conditions.
FANG-JENQ CHEN, MUJEEB MALIK, IVAN BECKWITH   +2 more
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Numerical Analysis of Axisymmetric Nozzle Aerodynamic Characteristics

Applied Mechanics and Materials, 2012
Abstract: Method of CFD is used to simulate flow fields for a certain Axisymmetric nozzle, The paper describes the grid adaption, boundary conditions determination as well as RNG model application, and analyzes the nozzle aerodynamic characteristics. The numerical results match well with test data.
Ping Wang, Xue Shan Liu, Yuan Da Wang, Xiao Kun Wang   +3 more
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Axisymmetric expansion of a gas from a nozzle into a vacuum

Journal of Fluid Mechanics, 1974
Using a test-particle Monte Carlo method the general features of a gas expanding from a circular nozzle into a vacuum were investigated. Calculations were performed by considering the flow to be uniform and axial at the exit plane of the nozzle with an exit Mach number of 3 and a throat Reynolds number of 25. Results are presented for the density, mean
Tuer, Thomas W., Springer, George S.
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Study on transonic tone in an axisymmetric supersonic nozzle

Journal of Thermal Science, 2010
This paper describes experimental and numerical works to investigate noise phenomenon in supersonic flow discharged from a convergent-divergent nozzle. The noise phenomenon of flow is generated by an emission of ‘transonic tones’. The results obtained show that the frequency of a transonic tone, that differs from the frequency of a screech tone due to ...
M. Yonamine, S. Jung, T. Aoki
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