Analysis of hypersonic ramjet cycles shows that supersonic combustion is requirement; paper presents experimental results where supersonic combustion in constant area duct is initiated by shock wave, evaluates possibility of analyzing data with one-dimensional flow equations, determines how closely current chemical kinetic computations agree with experimental results, and discusses problems encountered; shock-induced combustion is experimentally feasible in ducted flow, and can be controlled by varying inlet temperature, pressure, Mach number, on fuel concentration.
Shock-induced supersonic combustion in constant-area duct
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 2 , n 2
1965
7 pages
Article (Journal)
English
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