Results 181 to 190 of about 17,991 (229)

SUB-ALFVENIC INLET BOUNDARY CONDITIONS FOR AXISYMMETRIC MHD NOZZLES

37th AIAA Plasmadynamics and Lasers Conference, 2006
There are numerous electromagnetic accelerator concepts which require plasma expansion through a magnetic nozzle. If the inlet flow is slower than one or all of the outgoing characteristics, namely, the Alfven, slow and fast magnetosonic speeds, then the number of inlet conditions which could be arbitrarily specified are reduced by the number of ...
J T Cassibry, S T Wu
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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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Aeroacoustics of axisymmetric single and dual flow exhaust nozzles

13th Propulsion Conference, 1977
A systematic approach to the prediction of jet noise has been developed for conical, conventional bypass, and inverted-flow bypass nozzles. The prediction involves computation of the mean velocity, temperature, and relevant turbulence properties throughout the jet. Each turbulent eddy volume in the jet is treated as a statistically independent radiator
Philip R. Gliebe, Thomas F. Balsa
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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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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, 1971
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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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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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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Global smooth axisymmetric Euler flows with rotating effect in an infinitely long axisymmetric nozzle

Monatshefte für Mathematik, 2022
zbMATH Open Web Interface contents unavailable due to conflicting licenses.
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Comparison of Non-Axisymmetric & Axisymmetric Nozzles Installed on a V/STOL Fighter Model

SAE Technical Paper Series, 1977
<div class="htmlview paragraph">An experimental program sponsored by the Air Force Flight Dynamics Laboratory, utilizing a 1/8th scale advanced twin engine, thrust vectoring V/STOL fighter wind tunnel jet effects model developed for the Naval Air Propulsion Test Center, was completed in June of 1977 at the Arnold Engineering Development Center ...
W.C. Schnell, R.L. Grossman, G.E. Hoff
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