Abstract
The effect of allowing partial premixing of fuel and air before combustion heat release takes place is investigated for supersonic combustion of hydrogen in air. This premixing leads to a sharp, explosive, pressure rise at combustion. Attention is focussed on the thnist generated with a simple combustion chamber-thrust nozzle combination at approximate pre-combustion temperatures of 1100 K. The occurrence of the explosive pressure rise in the combustion chamber depends on a parameter involving the flow velocity and the pressure, as well as the length of the combustion chamber. Thrust production is inhibited when the value of this parameter is too low to allow the explosive pressure rise to develop in the combustion chamber.
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