Searched for: subject:"jet%5C+flow"
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document
Violato, D.V. (author)
To meet the increasingly stringent noise regulation, aircraft manufacturers are searching for solutions to jet noise. This, which constitutes a significant amount of the total noise emitted by civil aircrafts, is generated by the mixing processes between the exhaust flow leaving the engine and the atmosphere. A detailed understanding of such...
doctoral thesis 2013
document
Novara, M. (author)
This research deals with advanced developments in 3D particle image velocimetry based on the tomographic PIV technique (Tomo-PIV). The latter is a relatively recent measurement technique introduced by Elsinga et al. in 2005, which is based on the tomographic reconstruction of particle tracers in three-dimensional space from a small number of its...
doctoral thesis 2013
document
Slot, H.J. (author), Moore, P. (author), Delfos, R. (author), Boersma, B.J. (author)
In this paper we present the experimental results of a detailed investigation of the flow and acoustic properties of a turbulent jet with Mach number 0·75 and Reynolds number 3·5 103. We describe the methods and experimental procedures followed during the measurements, and subsequently present the flow field and acoustic field. The experiment...
journal article 2009
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Hoffmans, G.J.C.M. (author)
Het handboek ontgrondingen beoogt een instrument te zijn om de grootte van lokale ontgrondingskuilen rondom brugpijlers, kribben, achter drempels met of zonder bodembescherming, uitlaatconstructies, strandmuren, strandhoofden, etc. te voorspellen. Met het handboek kunnen ontwerpers en adviseurs een eerste schatting van het ontgrondingsproces...
report 1994
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de Wolf, W.B. (author), Munniksma, B. (author)
An experimental investigation was carried out concerning the effect of jet heating and external flow on the mean flow properties of a subsonic jet. A 60 mm diameter jet was tested in a wind tunnel at wind speeds of 0 and 60 m/s. Jet mach numbers varied between O.44 and 0.94 and jet total temperatures were 310 and 86O K. Velocity and temperature...
report 1980
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Zandbergen, T. (author), Maarsingh, R.A. (author)
Based on comparison with results from special experiments, an evaluation has been performed of the method of Levinsky, Thommen, Yager and Holland, which is intended to calcxilate the spanwise lift distribution on wings immersed in propulsive jets. Various modifications of the original method have been investigated. It was found that the method,...
report 1979
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Kho, Y.G. (author)
This report describes a wind-tunnel investigation on the interference between a jet and a wing half model, located outside the jet. Pressure distributions on the wing, and lift coefficients calculated from those have been used for evaluation of a method developed at NLR for the prediction of interference effects between jets and parts of...
report 1977
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Zandbergen, T. (author), Maarsingh, R.A. (author), Joosen, C.J.J. (author)
With the intent to test the qualities of the theoretical models used in two different calculation methods, pressure distributions have been measured on a simple half model wing-in-jet combination. The position of the jets relative to the wing was varied, mainly in a plane perpendicular to the span. Jet velocities of 1, 2 and 3 times the tunnel...
report 1977
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Snel, H. (author)
A brief description is given of a method, developed at NLR for the prediction of interference effects between (propulsion) jets and parts of airframes. The jet flow region is described by a model for a jet in a nonuniform mainflow, accounting for the presence of the airframe. The potential flow field around the airframe-jet combination is...
report 1976
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Snel, H. (author)
A model is derived for the calculation of the properties of a jet exhausting into a non-uniform main flow, at an arbitrary angle to the initial jet direction. The model is a generalisation of an earlier jet-ina-main flow model for uniform main flows. Semi empirical input is limited to an entrainment relation and a relation for form factors of...
report 1975
Searched for: subject:"jet%5C+flow"
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