Experimental and theoretical studies are being conducted to explore techniques to enhance mixing in scramjet combustors using parallel fuel injection from the base of swept and unswept wall-mounted ramps. Parallel injection may be useful in high speed scramjets due to the thrust contributed by the momentum of expanding fuel that has been heated in the vehicle cooling cycle. The experiments reported herein were conducted using Mach 2 and 3 combustor inlet conditions. Supporting computational and cold flow studies indicated that the observed enhanced mixing for the swept ramp configuration is primarily due to the substantially higher degree of vorticity and entrainment generated by the swept trailing edges.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Mach 2 and Mach 3 mixing and combustion in scramjets


    Contributors:

    Publication date :

    1991-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Application of Boundary Layer Combustion in High-Mach-Number Scramjets

    Peng, Yuan / Xu, Jinglei / Chen, Kuangshi | AIAA | 2024


    Wall Injectors for High Mach Number Scramjets

    Grossman, Peter / Maddalena, Luca / Schetz, Joseph | AIAA | 2006


    Wall Injectors for High Mach Number Scramjets

    Grossman, P. / Maddalena, L. / Schetz, J. et al. | British Library Conference Proceedings | 2006


    Supersonic mixing and combustion in scramjets

    Northam, G. B. / Capriotti, D. P. / Byington, C. S. et al. | NTRS | 1991