Yang, L and Erdem, E and Zare-Behtash, H and Kontis, K and Saravanan, S (2012) Pressure-sensitive paint on a truncated cone in hypersonic flow at incidences. In: International Journal of Heat and Fluid Flow, 37 . pp. 9-21.
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The flow over a truncated cone is a classical and fundamental problem for aerodynamic research due to its three-dimensional and complicated characteristics. The flow is made more complex when examining high angles of incidence. Recently these types of flows have drawn more attention for the purposes of drag reduction in supersonic/hypersonic flows. In the present study the flow over a truncated cone at various incidences was experimentally investigated in a Mach 5 flow with a unit Reynolds number of 13.5Ã�10 6m -1. The cone semi-apex angle is 15Â° and the truncation ratio (truncated length/cone length) is 0.5. The incidence of the model varied from -12Â° to 12Â° with 3Â° intervals relative to the freestream direction. The external flow around the truncated cone was visualised by colour Schlieren photography, while the surface flow pattern was revealed using the oil flow method. The surface pressure distribution was measured using the anodized aluminium pressure-sensitive paint (AA-PSP) technique. Both top and sideviews of the pressure distribution on the model surface were acquired at various incidences. AA-PSP showed high pressure sensitivity and captured the complicated flow structures which correlated well with the colour Schlieren and oil flow visualisation results. Â© 2012 Elsevier Inc.
|Item Type:||Journal Article|
|Additional Information:||Copyright for this article belongs to Elsevier|
|Keywords:||Pressure-sensitive paint;Hypersonic flow;Oil flow;Surface pressure mapping;Shock wave|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||18 Sep 2012 07:32|
|Last Modified:||04 Jan 2013 10:56|
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