Topic
Rocket
About: Rocket is a research topic. Over the lifetime, 14018 publications have been published within this topic receiving 95852 citations. The topic is also known as: rockets.
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TL;DR: In this article, the authors compared the performance of a conical axial injector of the oxidiser with a radial injector in terms of average and instantaneous regression rate, fuel consumption profiles, and combustion efficiency and stability.
46 citations
TL;DR: Electroimmunoassay (EIA) or rocket immunoelectrophoresis gives rapid and precise identification and quantification of even minor amounts of proteins.
Abstract: When electrophoresis of an antigen is performed in an agarose gel containing the corresponding antibody, a rocket-like immunoprecipitate develops [397,402,404]. The length of the rocket is linearly correlated to the amount of antigen. Electroimmunoassay (EIA) or rocket immunoelectrophoresis gives rapid and precise identification and quantification of even minor amounts of proteins. The coefficient of variation of double determinations is 1-5%. The electrophoretic run can be done in 2-16 h depending on the electrophoretic mobility of the antigen and the field strength used. An ultrarapid method is described in Chapter 23.
46 citations
TL;DR: In this article, a Bennett radio-frequency mass spectrometer was used to measure the ion composition of the upper atmosphere in the range 8 to 49 atomic mass units (AMU).
Abstract: The ambient positive-ion composition of the upper atmosphere in the range 8 to 49 atomic mass units (AMU) was measured between 93 and 219 km by means of a Bennett radio-frequency mass spectrometer. The experiment was flown in the Navy Viking 10 rocket, launched from White Sands Proving Ground, Las Cruces, New Mexico, at 10h 00m MST, May 7, 1954. The most prominent ion peaks found between 93 and 124 km on the ascent were at 16, 26, 30, and 32 AMU. Other less prominent peaks occurred at 12, 18, 19, 21, 23, 38, and 45 AMU. From 124 to 219 km, ions of 16 and 32 AMU persisted. The results of this investigation are to be considered preliminary and need further verification, not only because the data were obtained from only one flight, but also because of complications introduced by a charge acquired by the rocket and by the evolution of gas from the rocket.
46 citations
TL;DR: In this article, a parametric numerical analysis of supercritical hydrogen flow in an asymmetrically heated rectangular channel with a high aspect ratio and various radii of curvature is performed by means of a Reynoldsaveraged Navier-Stokes solver for real fluids, which is validated against experimental data of heated and curved channel flow taken from open literature.
Abstract: DOI: 10.2514/1.B34163 Coolant-flow modeling in regeneratively cooled rocket engines fed with turbomachinery is a challenging task because of the high wall-temperature gradient, the high Reynolds number, the high aspect ratio of the channel cross section,andthecurvedgeometry.Inthepresentstudy,tobettercomprehendtheroleofthethrust-chambershapeof a rocket engine on the heat exchange, computations of supercritical hydrogen flow in single- and double-curvature channels are carried out. In particular, a parametric numerical analysis of the flow in an asymmetrically heated rectangular channel with a high aspect ratio and various radii of curvature is performed by means of a Reynoldsaveraged Navier–Stokes solver for real fluids, which is validated against experimental data of heated and curvedchannel flow taken from open literature. Results permit the effect of curvature on global heat transfer coefficient, pressure loss, and bulk temperature increase to be quantified.
45 citations