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Total pressure
About: Total pressure is a research topic. Over the lifetime, 5199 publications have been published within this topic receiving 66658 citations.
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TL;DR: In this article, a multi-objective design optimization of a supersonic compressor cascade was dealt with, where the objectives were to minimize the cascade total pressure losses and to maximize the static pressure ratio using a Pareto ranking criterion.
38 citations
01 Jan 1964
TL;DR: In this article, the effect of free-stream Mach numbers of 1.38 to 4.54 on the flow field around the injection port for secondary injection of a gas normal to a supersonic stream was studied in a series of wind tunnel experiments.
Abstract: The flow field around the injection port for secondary injection of a gas normal to a supersonic stream has been studied in a series of wind tunnel experiments. The experiments were conducted at free-stream Mach numbers of 1.38 to 4.54. Gaseous nitrogen, argon, and helium were injected through a circular hole or a transverse slot with sonic flow at the injection orifice. Data are presented which include static pressure distributions on the wall in the region of the injector, shock shapes, and injectant mass fraction, total pressure, and velocity profiles downstream of the injector. A scale parameter has been calculated, based on a simple, inviscid model of the flow field. This scale parameter gives a good general correlation of the data. Use of this scale parameter allows the prediction of a simple scaling law for the normal forces on a wall produced by secondary injection. For the case of injection through a slot, this scaling law has been compared with experimental results reported by other workers. This comparison indicates that further work will be necessary to clarify the effect of free-stream Mach number on the flow field. For the case of injection through a hole, the force scaling law is in approximate agreement with existing rocket motor test results.
38 citations
TL;DR: In this article, the impact of non-steady outflow conditions on the compressor stator flow that is forced through a mimic in the wake of a linear low speed cascade to simulate the conditions that would be expected in a pulsed detonation engine was discussed.
Abstract: This contribution discusses the impact of a non-steady outflow condition on the compressor stator flow that is forced through a mimic in the wake of a linear low speed cascade to simulate the conditions that would be expected in a pulsed detonation engine. 2D/3C-PIV measurements were made to describe the flow field in the passage. Detailed wake measurements provide information about static pressure rise as well as total pressure loss. The stator profile used for the investigations is highly loaded and operates with three-dimensional flow separations under design conditions and without active flow control. It is shown that side wall actuation helps to stabilize the flow field at every phase angle and extends the operating range of the compressor stator. Furthermore, the static pressure gain can be increased by 6% with a 4% loss reduction in time averaged data.Copyright © 2015 by ASME
38 citations
TL;DR: In this article, a global mean profile for the PH3 vertical mixing ratio between 100 and 600 mbar total pressure was derived, consistent with a [P]/[H] ratio in the deep atmosphere that is about a factor of 10 higher than solar composition.
38 citations
TL;DR: An average loss in total pressure within a single bronchus was calculated after making several simplifying assumptions, and this result may be useful in modeling both the resistance of the entire bronchial tree and the more complex phenomenon of maximal expiratory flow.
Abstract: Static pressure differences across a human bronchial tree model were obtained for steady expiratory flows of several gases producing Reynolds numbers (Re1) in the bronchus carrying the entire flow (first bronchus) between 150 and 50,000. The model was constructed from an air-dried lung and was complete to bronchi about 2 mm in diameter. Dimensionless static pressure plotted against Re1 consolidated the data on a single curve, phenomenologically described by an equation of the form: delta Ps/delta Pd1 = A + B Re1 where delta P d1 is a pressure drop for Poiseuille flow, Velocity profile measurements at two sites along the first bronchus for laminar and turbulent flows indicate a dependence on the latter and distance from the first junction. Loss in total pressure was computed and may result from both frictional dissipation and changes in momentum flux associated with development of velocity profiles near the junctions. An average loss in total pressure within a single bronchus was calculated after making several simplifying assumptions, and this result may be useful in modeling both the resistance of the entire bronchial tree and the more complex phenomenon of maximal expiratory flow.
38 citations