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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Imprimer: 2150-766X
ISSN En ligne: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.340
pages 316-329

EXPERIMENTAL INVESTIGATION OF EROSIVE BURNING OF COMPOSITE PROPELLANTS UNDER SUPERSONIC CROSSFLOWS

S. Krishnan
Department of Aerospace Engineering Indian Institute of Technology Madras, Chennai-600 036, India
K. K. Rajesh
Department of Aerospace Engineering Indian Institute of Technology Madras, Chennai-600 036, India

RÉSUMÉ

Combustion products from a solid-propellant gas-generator are made to crossflow at transonic- and supersonic-velocities over the burning surface of a two-dimensional propellant-slab with a ramp at the slab-end — a nozzleless mode of operation. By using a high-speed camera, the burning edge of the propellant slab is observed under these crossflow conditions through a window assembly of polymethyl methacrylate. Presented are the erosive burning rates thus obtained for two composite propellants of the same composition but of different zero-crossflow burning rates (5- and 9-mm/s at 5 MPa). The erosive burning characteristics at transonic and supersonic crossflow conditions are mostly similar to those at subsonic crossflow situations.


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