Abstract
Flow separation control over a three-dimensional contour bump using jet in a Mach 1.9 supersonic free-stream has been experimentally investigated using a transonic/supersonic wind tunnel. Jet total pressure in the range of 0–4bar was blowing at the valley of the contour bump. Schlieren photography, surface oil flow visualisation and particle image velocimetry measurements were employed for flow visualisation and diagnostics. Experimental results show that blowing jet at the valley of the contour bump can hinder the formation and distort the spanwise vortices. The blowing jet can also reduce the extent of flow separation appears downstream of the bump crest. It was observed that this approach of flow control is more effective when high jet total pressure is employed. It is believed that a pressure gradient is generated as a result of the interaction between the flow downstream of the bump crest and the jet induced shock leads to the downwards flow motion around the bump valley.
Highlights
Research on two- and three-dimensional contour bumps is an active research topic in the aerospace sector because of their applicability in both transonic and supersonic vehicles
The stronger jet further distorted the spanwise vortex pair that results in the presence of the smaller spanwise vortices in the bump valley
This study experimentally investigated the flow patterns of the active jets bump with and without jet blowing in the bump valley
Summary
Research on two- and three-dimensional contour bumps is an active research topic in the aerospace sector because of their applicability in both transonic and supersonic vehicles. Later studies concluded that compared to the other conventional supersonic inlet configurations, DSI could achieve higher total pressure recovery and lower flow distortion in supersonic speeds [16,17,18,19,20]. The results from these studies eventually materialised and DSI was first implemented into the engines of the Lockheed-Martin F-35 Lightning supersonic fighter aircraft [21]
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