Numerical Simulation of the Effects of Mesoflaps in Controlling Shock/Boundary-Layer Interactions

Ghosh, Santanu; Edwards, Jack R.; Choi, Yung-Il

doi:10.2514/1.59758

Cited by 3 publications

(5 citation statements)

References 22 publications

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“…In contrast to the DES approaches, which switch from RANS to LES in separated flows away from walls, hybrid methods also treat attached flows, reducing the required computational resources with tailored near-wall RANS blended with LES away from the surface. A series of publications by Edwards et al describes the evolution of the procedure for different types of flows, including SBLI [133][134][135][136]. The corresponding required extension to the upstream profile generation approach based on recycling-rescaling is presented in Ref.…”

Section: Heat Transfer and Skin Friction Coefficientmentioning

confidence: 98%

“…Experimental results indicate that certain arrays of such devices could yield significant improvements in pressure recovery of a normal shock interaction. Ghosh et al [136] simulate this flow using an immersed boundary method and RANS and hybrid RANS/LES models. Their results suggest that for the configuration tested, there is a possibility of a connection between the dominant frequency of the flap and the low frequency shock motion and further that the axial separation is not substantially influenced by the control system.…”

Section: Controlmentioning

confidence: 99%

See 1 more Smart Citation

Progress in shock wave/boundary layer interactions

Gaitonde

2015

Progress in Aerospace Sciences

497

126

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Section: Heat Transfer and Skin Friction Coefficientmentioning

confidence: 98%

Section: Controlmentioning

confidence: 99%

Progress in shock wave/boundary layer interactions

Gaitonde

2015

Progress in Aerospace Sciences

497

126

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“…This immersed-boundary method is suitable for high-speed turbulent flows and has been used previously with success to simulate flows with similar flow-control devices. 9,10,13,17 The L 2 norm of the residual and the net mass balance are monitored for checking the convergence of the solution. The solution is considered converged when the normalized residual -with respect to the starting residual -reaches a value of about 1.0E − 08.…”

Section: Computational Methodologymentioning

confidence: 99%

“…In the recent past -about last two decades -a lot of research has been done 1-13 to design, understand, and evaluate alternate forms of flow control. This includes use of devices like vortex generators (wedges, vanes, and doublets) 5, 7-9, 11 , aero-elastically deflecting flaps [2][3][4]10 , and jets 6 of fluids among other devices. A majority of the numerical simulations/experiments performed to investigate and design such devices have used idealized computational domains with periodic boundary conditions in the spanwise direction 2,7,8,11,13 / ignored effects of wind-tunnel sidewalls [3][4][5] in wind-tunnel test sections.…”

Section: Introductionmentioning

confidence: 99%

Flow Control in a Mach 4.0 Inlet by Slotted Wedge-shaped Vortex Generators

Varma

Saurav

Ghosh

2015

33rd AIAA Applied Aerodynamics Conference

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This work investigates the effectiveness of a relatively novel flow control device, the slotted vortex generator, in mitigation of shock-induced flow separation in a realistic mixedcompression inlet geometry. The presence of sidewalls in an actual inlet makes the interactions between the oblique shocks and the boundary layers highly three dimensional. As such the flow separation and its control in a real inlet is more involved than that investigated based on notions of a primarily 2-D separation region. This work makes an attempt to determine an effective streamwise and spanwise arrangement of vortex generators in an actual inlet to minimize the flow separation. The inlet considered for the simulations are based on the experiments conducted by Emami and co-workers at NASA Glenn research center at Mach 4.03 to determine performance of an inlet/isolator configuration. The present work uses a computational domain for one such inlet configuration -having the smallest sized cowl -and a large convergence angle to produce a strong cowl lip shock. The computations performed are computed using the REACTMB code suitable for high-speed turbulent flows. The turbulence model used is Menter's SST model.

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“…A series of publications by Edwards et al describes the evolution of the procedure for different types of flows, including SBLI. [131][132][133][134] The corresponding required extension to the upstream profile generation approach based on recycling-rescaling is presented in Ref. 135.…”

Section: Heat Transfer and Skin Friction Coefficientmentioning

confidence: 99%

Progress in Shock Wave/Boundary Layer Interactions

Gaitonde

2013

43rd Fluid Dynamics Conference

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Recent advances in shock wave boundary layer interaction research are reviewed in four areas: i) understanding low frequency unsteadiness, ii) heat transfer prediction capability, iii) phenomena in complex (multi-shock boundary layer) interactions and iv) flow control techniques. Substantial success has been achieved in describing the phenomenology of low frequency unsteadiness, including correlations and coherent structures in the separation bubble, through complementary experimental and numerical studies on nominally 2-D interactions. These observations have been parlayed to propose underlying mechanisms based on oscillation, amplification and upstream boundary layer effects. For heat transfer prediction capability, systematic studies conducted under the auspices of AFOSR and RTO-AVT activities have shown that for axisymmetric laminar situations, heat transfer rates can be measured and in some cases be predicted reasonably accurately even in the presence of high-temperature effects. Efforts have quantified uncertainty of Reynolds averaged turbulence models, and hybrid methods have been developed to at least partially address deficiencies. Progress in complex interactions encompass two of the major phenomena affected by SBLI in scramjet flowpaths: unstart and mode transition from ramjet (dual mode) to scramjet. Control studies have attempted to leverage the better understanding of the fundamental phenomena with passive and active techniques, the latter exploiting the superior properties of newer actuators. Of interest are not only reduction in separation and surface loads, but also the spectral content. Finally, SBLI studies have benefited handsomely from successful ground and flight test campaigns associated with the HIFiRE-1 and HIFiRE-2 campaigns, results from which which are woven into the discussion, as are limitations in current capability and understanding.

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Numerical Simulation of the Effects of Mesoflaps in Controlling Shock/Boundary-Layer Interactions

Cited by 3 publications

References 22 publications

Progress in shock wave/boundary layer interactions

Progress in shock wave/boundary layer interactions

Flow Control in a Mach 4.0 Inlet by Slotted Wedge-shaped Vortex Generators

Progress in Shock Wave/Boundary Layer Interactions

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