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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.


Papers
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Journal ArticleDOI
TL;DR: In this article, phase equilibrium data, obtained by the quenching technique, are presented for the liquidus temperature region of the system iron oxide-Cr2O3-SiO2 in air, which represents an O2 isobaric section (po2= 0.21 atm.) through the quaternary system Fe-Cr-Si-O at a total pressure of 1 atm.
Abstract: Phase equilibrium data, obtained by the quenching technique, are presented for the liquidus temperature region of the system iron oxide-Cr2O3-SiO2 in air, which represents an O2 isobaric section (po2= 0.21 atm.) through the quaternary system Fe-Cr-Si-O at a total pressure of 1 atm. The diagram is dominated by a large area of coexistence of two immiscible liquids, and high liquids temperatures prevail throughout most of the system. Possible applications to refractory problems are indicated.

20 citations

Journal ArticleDOI
TL;DR: In this paper, the effectiveness of different flow control methods applied to a serpentine intake was evaluated with respect to static pressure recovery, total pressure loss and circumferential distortion at the exit.

20 citations

Patent
16 Nov 2001
TL;DR: In this article, the authors proposed a failure detection method based on at least two probes located on the skin of the aircraft, each probe comprising means for measuring the local incidence (αloc i αloc j), which consists in determining the incidence and/or the side slip (β) of an aircraft.
Abstract: The invention concerns a method for determining aerodynamic parameters of an air stream surrounding an aircraft The method, based on at least two probes located on the skin of the aircraft, each probe comprising means for measuring the local incidence (αloc i αloc j), consists in determining the incidence (α) and/or the side slip (β) of the aircraft, based on the local incidence of each probe et on the aerodynamic field of the aircraft The invention also concerns a method for detecting failure in a probe used for determining the aerodynamic parameters of the air stream surrounding an aircraft Said failure detection method consists in: determining for the set of the two probe blocks: the incidence and/or side slip on the basis of the local incidences and on the aircraft aerodynamic field; different pressure coefficient values of each probe based on the local incidence of each probe and on the aircraft aerodynamic field; the upstream infinite static pressure based on the pressure coefficient and the local static pressure of one and the same probe and based on a total pressure measurement; in comparing between them the upstream infinite static pressure, the incidence values and/or the side slip values

20 citations

Journal ArticleDOI
TL;DR: In this article, two kinds of cross-linked quaternized chitosan ( q -chito) membranes were used for high temperature and high pressure evapomeation.

20 citations

01 Nov 1973
TL;DR: In this paper, the results from testing of a 0.3 scale model center duct inlet (S duct) for the Pratt and Whitney Aircraft JT8D-100 engines are presented.
Abstract: The results from testing of a 0.3 scale model center duct inlet (S duct) for the Pratt and Whitney Aircraft JT8D-100 engines are presented. The objective of this test was to demonstrate that the required airflow of the JT8D-100 engine (480 lb/sec as compared to 334 lb/sec for JT8D-15) can be achieved with minimum modifications to the existing 727 airplane structure at acceptable levels of total pressure recovery and distortion. Steady-state pressure recovery, steady-state pressure distortion, and dynamic pressure measurements were taken at the engine face station. Surface static pressure measurements were taken along the duct. Test results indicated that the required airflow was achieved with acceptable pressure recovery (comparable to the current 727-200 S duct). Inlet inflow angle variation within the 727 airplane operating regime (minus 5 to 5 degrees) had no effect on the inlet performance. Pressure distortion at static and forward speed at takeoff airflow conditions are within P and WA limits for the Phase II duct when equipped with vortex generators. Static crosswind operation between 10 knots and 25 knots appears feasible at full takeoff power.

20 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202316
202225
2021127
2020147
2019153
2018128