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In this paper, a new solid rocket scramjet equipped with two combined cavity and strut device was studied by experimental and numerical approaches. The experiment simulated a flight Mach number 5.5 at 23 km. Hydrocarbon type fuel was used as the solid fuel-rich propellant. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport turbulence model are employed to simulate the flow field in the solid rocket scramjet combustor. The numerical method was validated by experimental data. The experimental results show that the combined cavity and strut device can play a role as ignition and flame holding in the solid rocket scramjet combustor. Additionally, the numerical results show that the combustion of gas and particle phase is conducted sequentially rather than simultaneously. And the total combustion efficiency mainly depends on the particle combustion. The total combustion efficiency is about 0.7 and the total pressure recovery is about 0.25 in this test. The combined cavity and strut device do improve the combustion efficiency in the solid rocket scramjet. However, the total pressure recovery is a rather low. Aerodynamic configuration optimization of the combined cavity and strut device will be carried out in the next step.
Flowfield structures of pylon-aided fuel injection of a sonic jet into a supersonic crossflow with Ma = 2.95 have been investigated by Nanoparticle-based Planar Laser Scattering (NPLS) technique and oil flow technique, seperately. Two experimental cases have been done for jet-to-crossflow momentum flux ratios (J) of 7.7 and 20.6, respectively, and the results are compared with those obtained by normal injection of a single jet from a flat plate without a pylon. Experimental results indicate that the flow structures of pylon-aided injection cases are very similar to those found in the normal injection cases in the downstream region of the jet. Upstream of the jet orifice, the detached shock generated at the leading edge of the pylon is identified by inserting with the separation shock. For lower injection pressure case there is always larger influences of the pylon in the flow structures in terms of jet plums’ position and the shock intensity. Besides, the mechanism of mixing enhancement resulting from the pylon is also elaborated in the present work.