Jan Siemen Smink, Sem de Maag, Cor. W. Lerink, Ella Giskes, Harry W.M. Hoeijmakers, Cees H. Venner, Frans B. Segerink, Herman L. Offerhaus

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-326

In order to minimize the length of supersonic-combustion ramjets (scramjets), injected fuel should mix
rapidly with the supersonic crossflow. Tandem dual jet injection shows improved mixing performance
over single jet injection. However, experiments on mixing by tandem dual jet injection have not yet
addressed the jet shear layer, in which the mixing occurs. The paper reports on investigation of the jet
shear layer, in a continuous air-indraft supersonic wind tunnel, at a Mach number around 1.6. A
Schlieren set-up has been realised for recording images of the flow features. A largely-automated
algorithm for processing Schlieren images has been developed to determine the location of the upper
boundary of the jet shear layer. The penetration of the jet is studied as function of two parameters (i)
𝐽, the ratio of the momentum of the jet and that of the crossflow and (ii) the nondimensionalized
distance 𝑆 between the dual jets. An empirical similarity relation has been established for the timeaveraged location of the jet upper shear layer as function of 𝐽 and 𝑆 covering the investigated conditions
(𝐽 = 2.8, 3.8 and 4.8 while 𝑆 = ∈ [0: 9.87]). The found empirical relationship has been validated for lower
and for higher values of 𝐽. The empirical similarity relation provides π‘†π‘œπ‘π‘‘, the spacing for maximal
penetration of the jets, as function of 𝐽.

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In Categories: 1.Events, HiSST 2022, Propulsion Systems and Components
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