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Numerical Simulation of Super-Detonative Ram Accelerator; Its Shock-Induced Combustion and Oblique Detonation

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Hypervelocity Launchers

Part of the book series: Shock Wave Science and Technology Reference Library ((SHOCKWAVES,volume 10))

Abstract

Hypersonic propulsion has been subjected to an intense research for the future propulsion. Various techniques have been proposed to replace the existing techniques. Most of them are chemical propulsion system, in which combustion plays a vital role in heat addition and its conversion to kinetic energy. The Ram Accelerator [1, 2], (referred to as RamAc), a ramjet-in-tube concept, is a propulsion concept based on using the Shock-Induced Combustion (SIC) to accelerate the projectile to a very high velocity. In a Ram accelerator, a projectile travels at supersonic speed in a launch tube, filled with a premixed fuel-oxidizer mixture

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Notes

  1. 1.

    Overdrive factor—ratio of projectile velocity to that of the C-J detonation velocity: the velocity at which the detonation propagates at the same velocity at which the reacting gas reaches sonic velocity as the reaction ceases.

  2. 2.

    xp—Distance traveled by the projectile in laboratory frame.

  3. 3.

    Thrust Coefficient is defined here as the ration of the thrust acting on the body and the initial pressure on the projectile cross section.

  4. 4.

    French-German Research Institute of Saint Louis, France.

  5. 5.

    More detailed discussion on the effect of Damköhler number (Da1) and Heat Release parameter are discussed by Choi et al. in Ref. [22].

  6. 6.

    ZND—the flow in which a high speed flow causes a thin reactionless shock wave followed by the reaction zone because of high temperature and aerodynamic compression of the mixture.

Abbreviations

HR:

Heat Release Parameter

ID:

Induction Distance

ODW:

Oblique Detonation Wave

OSW:

Oblique Shock Wave

NDW:

Normal Detonation Wave

SCRamAc:

Super detonative Combustion Ram Accelerator

SBLI:

Shock Boundary Layer Interaction

SCRamAc:

Super detonative Combustion Ram Accelerator

SD:

Shock Standoff Distance

SIC:

Shock-Induced Combustion

TC:

Thrust Coefficient

ZND:

Zeldovich, von Neumann and Döring Model

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Acknowledgements

Authors appreciate greatly P. Pradeep Kumar for editing the manuscript with great care. Authors also thank to F. Seiler and O. Igra and for suggesting this great opportunity, reading the manuscript and giving corrections.

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Authors and Affiliations

  1. Department of Aerospace Engineering, Pusan National University, 609-735, Busan, South Korea

    Jeong-Yeol Choi

  2. Department of Aerospace Engineering, Seoul National University, 151-744, Seoul, South Korea

    In-Seuck Jeung

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Correspondence to Jeong-Yeol Choi .

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Editors and Affiliations

  1. Karlsruhe Institute of Technology (KIT), Institute of Fluid Mechanics (ISTM), Karlsruhe, Germany

    Friedrich Seiler

  2. Department of Mechanical Engineering, Ben Gurion University of the Negev, Beer Sheva, Israel

    Ozer Igra

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Choi, JY., Jeung, IS. (2016). Numerical Simulation of Super-Detonative Ram Accelerator; Its Shock-Induced Combustion and Oblique Detonation. In: Seiler, F., Igra, O. (eds) Hypervelocity Launchers. Shock Wave Science and Technology Reference Library, vol 10. Springer, Cham. https://doi.org/10.1007/978-3-319-26018-1_9

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  • DOI: https://doi.org/10.1007/978-3-319-26018-1_9

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