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• W1263635 abstract "An experimental and theoretical investigation into single and intersecting swept, normal shock wave and expansion fan interactions with a turbulent boundary layer is reported. Experiments that were performed at a freestream Mach number of 1.85 involved measurements of surface pressures and surface heat transfer distributions and the recording of limiting streamline patterns. Analyses are presented for the development of single shock interactions and for the prediction of limiting streamline patterns in both single and intersecting wave interactions.  The experimental results suggest that the single shock interactions reach a fully developed form beyond about 20 boundary layer thicknesses from the shock generator. When account is taken of the boundary layer growth, this fully developed interaction has a cylindrically symmetric form. Surface pressure distributions are found to be consistent with the concept of spanwise propagation of disturbances along shock/boundary layer interaction characteristics. A model of the development of single shock interactions indicates that there is more rapid boundary layer thickening and greater cross-flow in the boundary layer towards the shock generator. This is consistent with experimental results. An analysis to predict limiting streamline deflection angles for single shock interactions, based on a cylindrically symmetric, triple-deck model, is developed. Qualitative predictions are in good agreement with experiments but quantitative results depend upon the value determined for the logarithmic decrement which is not predicted well. Surface heat transfer measurements indicate that the heat transfer rate is high towards the shock generator. Attempts to correlate the increase in heat transfer rate with the separation streamline from the nose of the shock generator were unsuccessful but increased heat transfer rates were noted close to the shock generator. Intersecting shock interactions are examined to determine their form. A superposition principle, which is inherent in the triple-deck model, can be used to predict the surface pressure distributions and limiting streamline patterns for intersecting shock interactions. Intersecting shock interactions can produce a given overall pressure rise with less likelihood of boundary layer separation than can an equivalent strength, 11 single shock interaction. A simple theory to predict limiting streamline deflection angles for single shock interactions is extended to boundary layer interactions with multiple, merging and intersecting shock and expansion fan configurations. Reasonable comparison with experiment is obtained for intersecting shock-shock and intersecting shock-expansion combinations. This theory indicates a slightly non-linear behaviour for these interactions with the prediction of converging or diverging limiting streamlines downstream of a wave intersection. An open-type separation is predicted for the converging limiting streamline cases. Both this theory and superposition suggest that the limiting streamline pattern for the intersection of a shock wave and an expansion fan can include a line of convergence upstream of the reflected shock wave. This may also lead to a form of open separation." @default.
• W1263635 created "2016-06-24" @default.
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• W1263635 date "1987-01-01" @default.
• W1263635 modified "2023-09-26" @default.
• W1263635 title "Investigation of swept shock wave boundary layer interactions" @default.
• W1263635 hasPublicationYear "1987" @default.
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