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Scramjet

About: Scramjet is a research topic. Over the lifetime, 4101 publications have been published within this topic receiving 51711 citations.


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Journal ArticleDOI
TL;DR: In this paper, a review of the evolution and maturity of SU-scramjet engines over the last 40 years is presented in terms of efforts completed or proceeding in the United States, Russia, France, Germany, Japan, Australia, and other countries.
Abstract: Ageneralreviewoftheemergenceandmaturingofsupersoniccombustionramjet (scramjet)enginetechnologies overthelast 40 years is presented. The review isgiven in terms of theeffortscompleted or proceeding in theUnited States, Russia, France, Germany, Japan, Australia, and other countries. A brief account of the challenges of scramjet combustor development is given, and attention is directed toward other source references for more detailed accounts of technology evolution. Two emerging scramjet applications are identie ed, namely, hydrogenfueledhigh-speed engines foraccess to spaceand hydrocarbon-fueled enginesforhypersonicair-launched missiles.

602 citations

Journal ArticleDOI
TL;DR: In this article, the authors describe ongoing research efforts in the scramjet community on cavity e ame holders, a concept for holding and stabilization in supersonic combustors, and discuss open questions impacting the effectiveness of the cavities as a holding device.
Abstract: This paper describes ongoing research efforts in the scramjet community on cavity e ame holders, a concept for e ame holding and stabilization in supersonic combustors. During the last few years, cavities have gained the attention of the scramjet community as a promising e ame-holding device, owing to results obtained in e ight tests and to feasibility demonstrations in laboratory-scale supersonic combustors. However, comprehensive studies are needed to determine the optimal cone guration that will yield the most effective e ame-holding capability with minimum losses. The e owe eld characteristics of cavities and research efforts related to cavities employed in lowand high-speed e ows are summarized. Open questions impacting the effectiveness of the cavities as e ame holders in supersonic combustors are discussed.

590 citations

Journal ArticleDOI
TL;DR: A general review of the worldwide evolution of ramjet propulsion since the Wright brothers first turned man's imagination into a practical reality is presented in this article, where the development history and principal contributing development programs are reviewed.
Abstract: A general review is presented of the worldwide evolution of ramjet propulsion since the Wright brothers e rst turned man’ s imagination to e y into a practical reality. A perspective of the technological developments from subsonic to hypersonic e ight speeds is provided to allow an appreciation for the advances made internationally from the early 1900s to current times. Ramjet, scramjet, and mixed-cycle engine types, and their operation and rationale for use are considered. The development history and principal contributing development programs are reviewed. Major airbreathing technologies that had signie cant impact on the maturation of ramjet propulsion and enabled engine designs to mature to their current state are identie ed. The general state of e ight-demonstrated technology is summarized and compared with the technology base of 1980. The current status of ramjet/scramjet technology is identie ed. Ramjet and scramjet propulsion technology has matured dramatically over the years in support of both military and space access applications, yet many opportunities remain to challenge future generations of explorers.

481 citations

Journal ArticleDOI
TL;DR: In this paper, a review of recent advances in boundary layer interaction research is presented, including low frequency unsteadiness, heat transfer prediction capability, complex (multi-shock boundary layer) interactions and flow control techniques.

435 citations

01 Feb 1988
TL;DR: In this article, a chemical kinetic mechanism for the combustion of hydrogen has been assembled and optimized by comparing the observed behavior as determined in shock tube and flame studies with that predicted by the mechanism.
Abstract: A chemical kinetic mechanism for the combustion of hydrogen has been assembled and optimized by comparing the observed behavior as determined in shock tube and flame studies with that predicted by the mechanism. The reactions contained in the mechanism reflect the current state of knowledge of the chemistry of the hydrogen/air system, and the assigned rate coefficients are consistent with accepted values. It was determined that the mechanism is capable of satisfactorily reproducing the experimental results for a range of conditions relevant to scramjet combustion. Calculations made with the reaction mechanism for representative scramjet combustor conditions at Mach 8, 16, and 25 showed that chemical kinetic effects can be important and that combustor models which use nonequilibrium chemistry should be used in preference to models that assume equilibrium chemistry. For the conditions examined the results also showed the importance of including the HO2 chemistry in the mechanism. For Mach numbers less than 16, the studies suggest that an ignition source will most likely be required to overcome slow ignition chemistry. At Mach 25, the initial temperature and pressure was high enough that ignition was rapid and the presence of an ignition source did not significantly affect reaction rates.

365 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
2023157
2022236
2021170
2020157
2019159
2018167