Effect of leading edge bluntness on the interaction of ramp induced shock wave with laminar boundary layer at hypersonic speed

John, Bibin; Kulkarni, Vinayak

doi:10.1016/j.compfluid.2014.03.004

Cited by 35 publications

(26 citation statements)

References 26 publications

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“…HLLC flux [11,12] is adopted for inviscid flux scheme and Green Gauss [13] for viscous flux scheme with a special accuracy of 1. Implicit time integration approach is used for obtaining numerical approximation of the solution, with the relaxation faction of 0.4 and the permissible range of CFL (Courant-Friedrichs-Lewy) [19,20] number is 0.09 -1.…”

Section: Computation Methodologymentioning

confidence: 99%

Hypersonic Flows Over Multi-Ramp Configurations

Sundarraj¹,

Güven²,

Kulkarni³

et al. 2019

IJRTE

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The effects of attaching multiple ramps to the standard double ramp configuration along with variations in ramp angle, free-stream Mach number and surface temperature are discussed in this investigation. This study investigates the changes associated with shock wave boundary layer interaction (SWBLI) due to ramp induced flow breakdown and the flow field fluctuation with changes in flow characteristics and design. This type of ramp junctions typically features in re-entry vehicles, engine intakes, system and sub-system junctions, control surfaces, etc. Ramp junctions usually are associated with strong separation bubble that has significant upstream influence impacting the effectiveness of aerodynamic surfaces, engine performance, thermal behavior and stability. Computation studies are carried out using Second order accurate, finite volume RANS solver considering compressible laminar flow characteristics, with solver settings provided like experimental conditions as per literature. Comprehensive double ramp studies with suggestions on reducing the separation bubble size are invariantly considered in literature, however there has been no study in understanding the inclusion of additional ramps in such flow scenarios. At the end of this study it was evident that such complex junction needs detailed understanding on how they benefit or impact the overall design of the system. It also gave a very good insight on the nature of flow around such complex junctions and instills motivation for detailed experimental understanding.

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Section: Computation Methodologymentioning

confidence: 99%

Hypersonic Flows Over Multi-Ramp Configurations

Sundarraj¹,

Güven²,

Kulkarni³

et al. 2019

IJRTE

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show abstract

“…Clemens and Narayanaswamy [29] surveyed the low-frequency unsteadiness of STBLIs in which they found that, upstream boundary layer fluctuations seem to be an important source of disturbances, but the evidence suggests that their impact is reduced by increasing the size of the separated flow. Effect of leading edge bluntness on the interaction of ramp induced shock wave with laminar boundary layer at hypersonic speed was investigated by John and Kulkarni [30]. They reported that, increasing the leading edge radius causes a growth in the separation bubble size.…”

Section: -Introductionmentioning

confidence: 98%

Wall modeled large eddy simulation of supersonic flow physics over compression–expansion ramp

Rad

Mousavi

2015

Acta Astronautica

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“…At such situations the design of the spacecraft is of prime importance. Various researchers [1][2][3][4][5][6][7][8][9][10] have investigated shock wave boundary layer and interaction physics through design modifications such as blunting, cavitation, ramping, flaring, external attachments such as aero disc or spike etc. to evaluate and understand the importance of these design features and also to measure the dependency on these features.…”

Section: Introductionmentioning

confidence: 99%

“…The SWBLI can produce separated flow at the upstream forward-facing corner where the deflection in the form of a ramp/flare is present. The length of separation has implications for control, stability etc., of a hypersonic reentry vehicle [4]. A separation shock wave is generated due to an abrupt change in flow direction in the presence of ramp.…”

Section: Introductionmentioning

confidence: 99%

“…This replacement leads to the formation of strong entropy layer and it interacts with the boundary layer. Flow over the object also gets accelerated due to favorable pressure gradient [4]. Hence a high-speed shear flow approaches the ramp which influences the location of separation bubble, bubble size, incipient separation angle and the reattachment point.…”

Section: Introductionmentioning

confidence: 99%

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Effect of Varying Ramp Angle and Leading-Edge Bluntness on the Behavior of Ramp Induced Shock Wave over Triple Ramped Cone Flare Configuration at Hypersonic Speed

Sundarraj¹,

Güven²,

Kulkarni³

et al. 2019

IJRTE

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Numerical simulation results are presented to show the effect of ramp angle variations and leading-edge bluntness on the flow around triple ramped cone flare in hypersonic flow. This study investigates the changes associated with shock wave boundary layer interaction due to ramp induced flow breakdown and the fluctuation in flow in the presence of blunted leading edge. This type of ramp junctions typically features in re-entry vehicles, engine intakes, system and subsystem junctions, control surfaces, etc. Ramp junctions usually are associated with strong separation bubble that has significant upstream influence impacting the effectiveness of aerodynamic surfaces, engine performance, thermal behavior and stability. Computation studies are carried out using finite volume-based RANS solver, accuracy of second order and considering compressible laminar flow characteristics, with solver settings provided similar to experimental conditions as per literature. Comprehensive double ramp studies with suggestions on reducing the separation bubble size are invariantly considered in literature, however there has been no study in understanding the inclusion of additional ramps in such flow scenarios, hence efforts are taken to understand the benefits and implications of including a third ramp along with varying bluntness on the bubble size and its upstream intensity

show abstract

Effect of leading edge bluntness on the interaction of ramp induced shock wave with laminar boundary layer at hypersonic speed

Cited by 35 publications

References 26 publications

Hypersonic Flows Over Multi-Ramp Configurations

Hypersonic Flows Over Multi-Ramp Configurations

Wall modeled large eddy simulation of supersonic flow physics over compression–expansion ramp

Effect of Varying Ramp Angle and Leading-Edge Bluntness on the Behavior of Ramp Induced Shock Wave over Triple Ramped Cone Flare Configuration at Hypersonic Speed

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