Experimental Characterization of Hypersonic Boundary Layer in Flight and in Wind-tunnel Condition

Experimental Investigation of Liquid Fragmentation In Hypersonic Crossflow

“…The results are strongly dependent of the testing time that has to be adapted to the test conditions. Just like oil visualization tests, sublimation experiments are recorded using the high-speed camera, only for 3-D obstacle experiments [143].…”

“…The results of the experiments are discussed in Section 5.2. The chapter is concluded by comparing the results with those of gas injection into Mach 6 cross flow (Section 5.3.1) [126,127] and also those of 3-D rigid obstacles in Mach 6 flow (Section 5.3.2) [143], performed by independent researchers [127,143] at the same facility and under similar conditions.…”

“…Despite its noise level, the H-3 wind tunnel is considered to be comparable to other well established hypersonic wind tunnels and therefore is seen as a suitable facility for hypersonic testing [143]. This facility is chosen for the experimental investigation of liquid fragmentation in high speed cross flow conditions because of its well defined and long duration Mach 6 flow envelope.…”

“…The boundary layer grows inside the entropy layer with a strong vorticity and it is affected by the presence of the entropy layer. This interaction is called vorticity interaction [6,143].…”

“…Because of all these considerations, it is of utmost importance to understand the flow topology around a 3-D rigid boundary (such as an isolated or distributed roughness element) within a hypersonic crossflow. Because of these reasons, the effects of 3-D rigid obstacles 1 in Mach 6 cross flow is studied by [143] in the H-3 wind tunnel facility of the von Karman Institute. The main results are discussed here for a comparison of the flow topology between liquid injection and 3-D obstacles within Mach 6 cross flow, exactly under the same conditions of the same wind tunnel.…”