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Hydrogen scramjet with sidewall injection - Shock tunnel simulations (1987)

Morgan, R. G. ; Stalker, R. J. ; Morris, N. ; [et al.]

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Publication Date: 2011-08-19

Description: A free-piston shock tunnel has been used to obtain test data on a scramjet combustion chamber with sidewall injection. The results obtained indicate that combustion was strongly influenced by a region of fuel whose temperature was held below its ignition temperature by wall-cooling effects; this increased the fraction of unburned fuel and resulted in a significant loss of specific impulse. Aerodynamic heating would keep the walls above hydrogen ignition temperature in an actual scramjet powerplant, however. Maximum specific impulse was obtained with a combination of parallel and transverse injection in a long combustion chamber, followed by a dual stage expansion.

Keywords: AIRCRAFT PROPULSION AND POWER

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