Studies on the influence of steady microactuators on shock-wave/boundary layer interaction

Ali, Mohd Y and Alvi, Farukh and Kumar, Rajan and Manisankar, C and Verma, SB and Venkatakrishnan, L (2013) Studies on the influence of steady microactuators on shock-wave/boundary layer interaction. AIAA Journal, 51 (12). pp. 2753-2762. ISSN 0001-1452

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An array of high-momentum microjets are used upstream of a compression corner to control the shock-wave/ boundary-layer interaction on a 24 deg unswept compression ramp in a Mach 2 flow. Measurements include schlieren flow visualization and unsteady pressure measurements using fast-response pressure sensors of the interaction region. Results show that the array of microjets issuing in the supersonic crossflow create oblique shocks, which effectively reduce the incoming Mach number at the compression corner. This leads to a modified separation shock of significantly reduced strength. The location of the modified shock is moved upstream by as much as 4δ0 from its mean undisturbed location. The mean pressure distribution on the surface is altered with microjet control leading to a more gradual compression of the incoming flow relative to the separation shock without control. The wall-pressure fluctuations in the interaction region are reduced by approximately 50%, and the flow near the compression corner appears to be energized with control, based on the unsteady surface-pressure measurements. The pressure spectra show that microjet control results in a redistribution of energy on the wall and the ramp surfaces.

Item Type: Article
Additional Information: Copyright to this article belongs to M/s. American Institute of Aeronautics and Astronautics
Uncontrolled Keywords: Microactuators on shock-wave;Microactuators on boundary-layer interaction;High-momentum microjets; Measurement uncertainties;Flow visualization
Subjects: AERONAUTICS > Aeronautics (General)
Depositing User: Ms. Alphones Mary
Date Deposited: 23 Jul 2015 07:47
Last Modified: 05 Aug 2015 08:39

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