Abstract
Thrust by scramjet nozzles was measured using a high-temperature gas flow with Mach 2.5 and a total temperature of 3100 K by combustion of monomethyl-hydrazine (MMH) and nitrogen tetraoxide (NTO). Wall pressure on the nozzles was monitored to estimate the pressure force on the nozzles. Series of cold nitrogen (N2) flow tests were also conducted using the same nozzles. An inviscid two-dimensional code was able to reproduce nozzle performance of the cold N2 flow. The calculations with chemical kinetics also predicted the experimental results of the MMH/NTO flow within an error of 3.6%. Kinetic, two-dimensional and friction losses in the scramjet nozzles were identified for the nozzle, and the scale effects of the nozzle performance of H2-fueled engines are discussed.
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