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Design and Analysis of a Mach 3 Dual Mode Scramjet Combustor

Corbin, Christopher Ryan

Abstract Details

2008, Master of Science in Engineering (MSEgr), Wright State University, Mechanical Engineering.
Low speed operation of a dual mode scramjet engine is important to the development of a two stage to orbit reusable launch vehicle. This study investigates the Mach 3 operation of a dual mode scramjet engine. SRGULL, a one-dimensional cycle code for scramjet engines, and VULCAN, a computational fluid dynamics code capable of solving reacting flows, are used in this study. Staged injection is investigated to allow more heat release at a low flight Mach number condition so that more thrust can be achieved and inlet unstart is avoided. The nominal case has one injector located 1.067 meters downstream of the inlet with a fuel equivalence ration of 0.488. An increase in thrust of 11.6% is shown in this study by injecting a fuel equivalence ratio of 0.437 upstream and a fuel equivalence ratio of 0.369 at a location 0.8 meters downstream of the first injector.
J. Mitch Wolff, PhD (Advisor)
Dean Eklund, PhD (Committee Member)
Richard Branam, PhD (Committee Member)
100 p.

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Citations

  • Corbin, C. R. (2008). Design and Analysis of a Mach 3 Dual Mode Scramjet Combustor [Master's thesis, Wright State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=wright1208370076

    APA Style (7th edition)

  • Corbin, Christopher. Design and Analysis of a Mach 3 Dual Mode Scramjet Combustor. 2008. Wright State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=wright1208370076.

    MLA Style (8th edition)

  • Corbin, Christopher. "Design and Analysis of a Mach 3 Dual Mode Scramjet Combustor." Master's thesis, Wright State University, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=wright1208370076

    Chicago Manual of Style (17th edition)