+publisher:"Indian Institute of Science" +contributor:("Ramesh, O N")

Indian Institute of Science

1. Ajit, Dixit Shivsai. Structure Of Sink Flow Boundary Layers.

Degree: 2009, Indian Institute of Science

URL: http://hdl.handle.net/2005/1098

► The work reported in this thesis is an experimental and theoretical investigation of the so-called sink flow boundary layers. These are two-dimensional (in the mean),… (more)

▼ The work reported in this thesis is an experimental and theoretical investigation of the so-called sink flow boundary layers. These are two-dimensional (in the mean), favourable-pressure-gradient (FPG) boundary layer flows where the boundary layers experience stream-wise acceleration inside a two-dimensional convergent channel with smooth and plane walls. The boundary layers studied are mainly turbulent with few cases that may be identified as reverse-transitional. The sink flow turbulent boundary layers (TBLs) are the only smooth-walled layers that are in ‘perfect equilibrium’ or ‘exact self-preservation’ in the sense of Townsend (1976) and Rotta (1962). The present boundary layer experiments were conducted in an open-return low-speed wind tunnel. The sink flow conditions were established on the test-plate by using a contoured test-section ceiling for creating a convergent channel with smooth and plane walls. The strength of the streamwise FPG was varied by changing the freestream speed in the test-section. Few zero-pressure-gradient (ZPG) turbulent boundary layers were also measured in the same tunnel for which the contoured ceiling was replaced by a straight one. The velocity measurement techniques used include conventional Pitot-tubes for mean flow measurements and hotwire/crosswire probes for turbulence measurements. For measurement of skin friction in ZPG flows, Preston-tube was used while for the sink flows the so-called surface hotwire method was employed. Static pressures were measured on the test-surface using an alcohol-based projection manometer. Boundary layers were tripped at the beginning of the test-plate to ensure quick transition to turbulence. The mean velocity scaling in sink flow TBLs in the presence of strong FPG has been studied systematically, especially in view of the apparent pressure-gradient-dependence of the logarithmic laws reported in the literature (Spalart & Leonard, 1986; Nickels, 2004; Chauhan et al., 2007). The experimental study of sink flow TBLs carried out over a wide range of streamwise FPGs has shown that the mean velocity profiles (in inner coordinates) exhibit systematic departures from the universal logarithmic law as the pressure gradient parameter ∆p is varied. Even so, each of these profiles exhibits a logarithmic region, albeit non-universal, whose constants are functions of the pressure gradient. Systematic dependence of these constants on the pressure gradient parameter ∆p is observed. Moreover, the wake region is uniformly absent in all these profiles. In other words, each profile looks like a ‘pure wall-flow’, in the sense of Coles (1957), only if it is viewed in relation to its own non-universal logarithmic law. To support the experimental observation of the pressure-gradient-dependence of logarithmic laws in sink flow TBLs, a theory based on the method of matched asymptotic expansions has been applied to sink flow TBLs and this theory reveals a systematic dependence of inner and outer logarithmic laws on the pressure gradient parameter ∆p. This dependence is… Advisors/Committee Members: Ramesh, O N.

Subjects/Keywords: Aerodynamics Boundary Layers; Turbulent Boundary Layers (TBLs); Laminar Flow; Boundary Layer Flows; Sink Flow Turbulent Boundary Layers; Skin Friction (Aerodynamics); Favourable Pressure-Gradient Boundary Layer Flows; Sink Flow Boundary Layers; Aeronautics

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APA (6^th Edition):

Ajit, D. S. (2009). Structure Of Sink Flow Boundary Layers. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1098

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ajit, Dixit Shivsai. “Structure Of Sink Flow Boundary Layers.” 2009. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/1098.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ajit, Dixit Shivsai. “Structure Of Sink Flow Boundary Layers.” 2009. Web. 12 Dec 2019.

Vancouver:

Ajit DS. Structure Of Sink Flow Boundary Layers. [Internet] [Thesis]. Indian Institute of Science; 2009. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/1098.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ajit DS. Structure Of Sink Flow Boundary Layers. [Thesis]. Indian Institute of Science; 2009. Available from: http://hdl.handle.net/2005/1098

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

2. Suhas, Diwan Sourabh. Dynamics Of Early Stages Of Transition In A Laminar Separation Bubble.

Degree: 2009, Indian Institute of Science

URL: http://hdl.handle.net/2005/679

► This is an experimental and theoretical study of a laminar separation bubble and the associated transition dynamics in its early stages. The separation of a… (more)

▼ This is an experimental and theoretical study of a laminar separation bubble and the associated transition dynamics in its early stages. The separation of a laminar boundary layer from a solid surface is prevalent in very many flow situations such as over gas turbine blades (especially in the low-pressure turbine stage) and the wings of micro-aero-vehicles (MAVs) that operate at fairly low Reynolds numbers. Flow separation occurs in such cases due to the presence of an adverse pressure gradient. The separated shear layer becomes unstable due to the presence of an inflection point and presumably transitions to turbulence rapidly. Eventually, there is reattachment back to the solid surface further downstream, if conditions are right. The region enclosed by the shear layer is called a laminar separation bubble and has been a subject of many studies in the past. The present experiments have been conducted in a closed-circuit wind tunnel. A separation bubble was obtained on the upper surface of a flat plate by appropriately contouring the top wall of the tunnel. Four different techniques were used for qualitative and quantitative study viz. surface flow visualisation, smoke flow visualisation, surface pressure measurements and hotwire anemometry. Response of the bubble to both natural as well as artificial (impulsive excitation) disturbance environment has been studied. Linear stability analyses (both Orr-Sommerfeld and Rayleigh calculations), in the spatial framework, have been performed for the mean velocity profiles starting from an attached adverse pressure gradient boundary layer all the way up to the front portion of the separation bubble region (i.e. up to the end of the dead-air region where linear evolution of disturbances could be expected). The measured velocity profiles (both attached and separated) were fitted with analytical model profiles for doing stability calculations. A separation bubble consists of aspects of both wall-bounded and wall-free shear layers and therefore both viscous and inviscid mechanisms are expected to be at play. Most of the studies in the literature point to the inviscid instability associated with the shear layer to be the main mechanism. The main aim of the present work is to understand the exact origin of the primary instability mechanism responsible for the amplification of disturbances. We argue that at least up to the front portion of the bubble, the instability mechanism is due to the inflectional mode associated with the mean velocity profile. However, the seeds of this inviscid inflectional instability could be traced back to the attached boundary layer upstream of separation. In other words, the inviscid inflectional instability of the separated shear layer should be logically seen as an extension of the instability of the upstream attached adverse-pressure-gradient boundary layer. This modifies the traditional view that pegs the origin of the instability in a separation bubble to the free shear layer outside the bubble with its associated Kelvin-Helmholtz mechanism. Our… Advisors/Committee Members: Ramesh, O N.

Subjects/Keywords: Laminar Boundary Layers; Bubbles; Transition Dynamics; Smoke Flow Visualization; Bubble Bursting; Separation Bubbles - Instability; Spatial Inviscid Instability; Laminar Separation Bubble; Parallel Flows; Gas Dynamics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Suhas, D. S. (2009). Dynamics Of Early Stages Of Transition In A Laminar Separation Bubble. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/679

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Suhas, Diwan Sourabh. “Dynamics Of Early Stages Of Transition In A Laminar Separation Bubble.” 2009. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/679.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Suhas, Diwan Sourabh. “Dynamics Of Early Stages Of Transition In A Laminar Separation Bubble.” 2009. Web. 12 Dec 2019.

Vancouver:

Suhas DS. Dynamics Of Early Stages Of Transition In A Laminar Separation Bubble. [Internet] [Thesis]. Indian Institute of Science; 2009. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/679.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Suhas DS. Dynamics Of Early Stages Of Transition In A Laminar Separation Bubble. [Thesis]. Indian Institute of Science; 2009. Available from: http://hdl.handle.net/2005/679

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

3. Malik, Bijoy Kumar. Study of Non-Equilibrium Flow Behind Normal Shock.

Degree: 2014, Indian Institute of Science

URL: http://etd.iisc.ernet.in/handle/2005/2891

► Normal shock problems in high enthalpy flows are of special interests to aerodynamicists and fluid dynamicists. When the shock Mach number become hypersonic and increasing… (more)

▼ Normal shock problems in high enthalpy flows are of special interests to aerodynamicists and fluid dynamicists. When the shock Mach number become hypersonic and increasing further, the gas passing through the shock is compressed resulting in increase in temperature and pressure. As the Mach number increases the internal degrees of freedom of the diatomic molecules are activated to an increasing extent when it crosses the shock resulting dissociation especially for high enthalpy flows. Hence dissociation of diatomic molecules must be taken into account in the determination of some of the aerodynamic parameters. This thermal and chemical process can be divided into three types such as nearly frozen, non-equilibrium and nearly non-equilibrium depending on the rates of reaction and excitation. For typical re-entry conditions of spacecrafts into a planets atmosphere, dissociation reactions of the molecules is dominant in the stagnation flow. Further in the stagnation region of the flow field one of the most important parameter that characterizes the flow field is the shock stand-off distance. This parameter is often employed for validation purposes of numerical methods as well as for non-reactive and reactive gases. For high Mach number flows the shock is very close to the body hence experimental determination of shock stand-off distance is very difficult and there would be relatively large errors. Therefore the theoretical determination of this parameter is of great significance in the discussion of this physical phenomenon. There are some works which presents how the dissociation behind shock affects the shock stand-off distance. Thus the dissociation behind the shock is a very important process which has great impact in aerodynamic flight and design. In this present work we studied how dissociation of diatoms occur behind a normal shock. Treanor and Marrone (1962) proposed CVD(coupled vibration-dissociation) model for diatoms by assuming diatom as a harmonic oscillator with a cut-off level. But actually diatoms are not harmonic oscillator, because spectroscopic data of energy level spacing is not like harmonic oscillator. For this reason, Treanor, Rich, and Rehm(1968) used anharmonic oscillator model for diatoms to study vibrational relaxation. Taking the anharmonicity of diatom, Philip Morse(1929) gave a formula for potential energy levels for diatoms, which is known to express the experimental values quite accurately. Unlike the energy levels of the harmonic oscillator potential, which are evenly spaced , the Morse potential level spacing decreases as the energy approaches the dissociation energy and then it is continuous. So it is quite accurate to take Morse oscillator theory for diatomic dissociation instead of harmonic oscillator with a cut-off level. We have used Morse oscillator theory to derive a dissociation-recombination reaction rate equation for diatom. To derive the rate equation we have used the transition probability between different vibrational energy levels . The rate equation is numerically solved… Advisors/Committee Members: Ramesh, O N.

Subjects/Keywords: Shock Waves; Supersonic Aerodynamics; Fluid Dynamics; Non-Equilibrium Flows; Unsteady Shock; An-harmonic Oscillator Theory; Diatomic Dissociation; Oscillator Model; Shock (Mechanics); Ionization; Morse Oscillator Theory; Shock Flow; Aerospace Engineering

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Malik, B. K. (2014). Study of Non-Equilibrium Flow Behind Normal Shock. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/2891

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Malik, Bijoy Kumar. “Study of Non-Equilibrium Flow Behind Normal Shock.” 2014. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/handle/2005/2891.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Malik, Bijoy Kumar. “Study of Non-Equilibrium Flow Behind Normal Shock.” 2014. Web. 12 Dec 2019.

Vancouver:

Malik BK. Study of Non-Equilibrium Flow Behind Normal Shock. [Internet] [Thesis]. Indian Institute of Science; 2014. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/handle/2005/2891.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Malik BK. Study of Non-Equilibrium Flow Behind Normal Shock. [Thesis]. Indian Institute of Science; 2014. Available from: http://etd.iisc.ernet.in/handle/2005/2891

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

4. Sarasija, S. Studies on Vortex Breakdown in a Closed Cylinder with a Rotating Endwall.

Degree: 2014, Indian Institute of Science

URL: http://etd.iisc.ernet.in/handle/2005/2985 ; http://etd.ncsi.iisc.ernet.in/abstracts/3847/G26720-Abs.pdf

► Swirling flows abound in nature and numerous engineering applications. Under conditions which are not completely understood, the swirling cores could undergo a sudden enlargement of… (more)

Subjects/Keywords: Vortex Breakdown; Vorticity; Helicity; Rotating Endwall; Vortex Breakdown-Closed Cylinder; Flow Visualization; Spiral Breakdown; Vortex Bursting; Fluid Mechanics; Inviscid Vortex Dynamics Model; Vorticity Vectors; Aerospace Engineering

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APA (6^th Edition):

Sarasija, S. (2014). Studies on Vortex Breakdown in a Closed Cylinder with a Rotating Endwall. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/2985 ; http://etd.ncsi.iisc.ernet.in/abstracts/3847/G26720-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Sarasija, S. “Studies on Vortex Breakdown in a Closed Cylinder with a Rotating Endwall.” 2014. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/handle/2005/2985 ; http://etd.ncsi.iisc.ernet.in/abstracts/3847/G26720-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Sarasija, S. “Studies on Vortex Breakdown in a Closed Cylinder with a Rotating Endwall.” 2014. Web. 12 Dec 2019.

Vancouver:

Sarasija S. Studies on Vortex Breakdown in a Closed Cylinder with a Rotating Endwall. [Internet] [Thesis]. Indian Institute of Science; 2014. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/handle/2005/2985 ; http://etd.ncsi.iisc.ernet.in/abstracts/3847/G26720-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Sarasija S. Studies on Vortex Breakdown in a Closed Cylinder with a Rotating Endwall. [Thesis]. Indian Institute of Science; 2014. Available from: http://etd.iisc.ernet.in/handle/2005/2985 ; http://etd.ncsi.iisc.ernet.in/abstracts/3847/G26720-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

5. Suneesh, S S. Experimental Studies on the Effect of an Upstream Periodic Wake on a Turbulent Separation Bubble.

Degree: 2016, Indian Institute of Science

URL: http://etd.iisc.ernet.in/2005/3762 ; http://etd.iisc.ernet.in/abstracts/4633/G28454-Abs.pdf

► The object of the present work is to experimentally study the case of a turbulent boundary layer subjected to an Adverse Pressure Gradient (APG) with… (more)

▼ The object of the present work is to experimentally study the case of a turbulent boundary layer subjected to an Adverse Pressure Gradient (APG) with separation and reattachment. The effect of unsteadiness on turbulent boundary layer separation by means two different methods were explored viz. the effect of local forcing by acoustic waves and effect of wakes on separation bubble. The experiments were conducted in a low speed open circuit blower type wind tunnel. The turbulent separation bubble was created on the test plate by a contoured ceiling which created the adverse pressure gradient. The velocities were measured using single element hot wire and X-wire. Limited studies on quasi shear stress were also conducted using surface mounted hot film probes. Static pressure was measured using a projection manometer. Boundary layer is tripped near the leading edge of the flat plate to ensure a turbulent boundary layer. Surface pressure distribution and flow visualization were conducted as part of diagnostics. In the case of laminar separation bubble, lot of investigations have been done on the effect of unsteady wake and the most important conclusion was that the wake induces `bypass' transition to turbulence and since the turbulent boundary layer is more resistant to separation, it remains attached. In the case of turbulent separation bubble, laminar-turbulent transition is not relevant and if the bubble is suppressed, it should be by some other mechanism. This is what we seek to unravel in this study. A closer look at the mean velocity profiles reveal the occurrence of inflection point before separation as in the case of laminar separation bubble and the peak values of turbulence intensities correspond to the location of point of inflection. Turbulent separation correlations proposed by various investigators were compared with the present results and are found to be in good agreement. Surface flow visualization pictures are used to get qualitative information. The wall forcing on the separation bubble was done using a speaker which blows a small amount of air when the diaphragm moves up and sucks in when the diaphragm moves down. The blowing effect seems to be more effective in suppressing the separation compared to suction. The interaction with wake is studied using an unsteady bar which is moving up and down. The inflection point in the mean velocity distribution seems to move closer to the wall with the impingement o the wake. Also the turbulence intensities have increased and seem to move closer to the wall. The displacement and momentum thickness have increased and the shape factor has decreased which indicates suppression of the bubble. The quasi shear stress in the separated region also increased which indicates suppression of separation. While the oncoming unsteady wake might be a parcel of fluid with defect velocity when seen in isolation, in comparison to the velocity defect in the separation bubble, it is a region of velocity excess. As a result, one can expect the impingement of the unsteady wake on the… Advisors/Committee Members: Ramesh, O N.

Subjects/Keywords: Turbulent Boundary Layer Separation; Wake Boundary Layer Interaction; Wind Tunnel; Turbulent Separation Bubble Structure; Turbulent Separation Bubble; Turbulent Boundary Layer; Adverse Pressure Gradient (APG); Phase Averaging Technique; Aerospace Engineering

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Suneesh, S. S. (2016). Experimental Studies on the Effect of an Upstream Periodic Wake on a Turbulent Separation Bubble. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/2005/3762 ; http://etd.iisc.ernet.in/abstracts/4633/G28454-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Suneesh, S S. “Experimental Studies on the Effect of an Upstream Periodic Wake on a Turbulent Separation Bubble.” 2016. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/2005/3762 ; http://etd.iisc.ernet.in/abstracts/4633/G28454-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Suneesh, S S. “Experimental Studies on the Effect of an Upstream Periodic Wake on a Turbulent Separation Bubble.” 2016. Web. 12 Dec 2019.

Vancouver:

Suneesh SS. Experimental Studies on the Effect of an Upstream Periodic Wake on a Turbulent Separation Bubble. [Internet] [Thesis]. Indian Institute of Science; 2016. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/2005/3762 ; http://etd.iisc.ernet.in/abstracts/4633/G28454-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Suneesh SS. Experimental Studies on the Effect of an Upstream Periodic Wake on a Turbulent Separation Bubble. [Thesis]. Indian Institute of Science; 2016. Available from: http://etd.iisc.ernet.in/2005/3762 ; http://etd.iisc.ernet.in/abstracts/4633/G28454-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

6. Patwardhan, Saurabh Sudhir. Effect of Favourable Pressure Gradient on Turbulence in Boundary Layers.

Degree: 2015, Indian Institute of Science

URL: http://etd.iisc.ernet.in/2005/3831 ; http://etd.iisc.ernet.in/abstracts/4703/G26983-Abs.pdf

► This thesis explores the effects of favourable pressure gradient on the structure of turbulent boundary layers (TBL). In this context, the structure of three types… (more)

▼ This thesis explores the effects of favourable pressure gradient on the structure of turbulent boundary layers (TBL). In this context, the structure of three types of boundary layers namely a zero-pressure-gradient boundary layer, equilibrium boundary layers under favourable pressure gradient and relaminarising boundary layers is investigated mostly from the point of view of large-scale dynamics. This covers a whole range of flows on the so-called Reynolds number - pressure gradient diagram - from turbulent zero pressure gradient flows to relaminarising flows at relatively low Reynolds numbers. The study of turbulent and relaminarising boundary layers is carried out primarily using direct numerical analyses and some limited experiments in this thesis. The direct numerical simulations (DNS) of a zero-pressure-gradient turbulent boundary layer (ZPG TBL) is validated against the experimental and DNS data available in the literature. Furthermore, the important question of time-averaged signature of a large scale vortex structure and its relation with the two-point correlations in the context of ZPG TBL is addressed. In this context, a synthetic flow consisting of hairpin vortex structures is generated. The two-point correlations in the synthetic TBL and a real TBL are found to be qualitatively similar. This shows that the vortex structure leaves a time-averaged footprint in the form of correlations of velocity and vorticity. A study of two-point correlations in a real TBL shows that the structure angle deduced from two-point correlations varies with wall-normal location. The structure angle is small near the wall and increases away from the wall in agreement with the previous studies. The small angle close to the wall signifies the presence of streamwise structure. Away from the wall, this streamwise coherence is lost and the correlation contours become more isotropic. The presence of the wall and the mean shear affects smaller scales making them anisotropic close to the wall. Towards the edge of the boundary layer, smaller scales tend to become isotropic leading to -5/3 law in the energy spectrum. Further, a relation between a passive scalar in a flow and vorticity is explored. It is found that the scalar product of vorticity and scalar gradient is conserved in a non-diffusive situation. This assertion is demonstrated under various flow conditions. Despite the differences in Schmidt numbers, the structures observed in the outer layer are similar in both numerical and experimental flow visualisations. Further, the equilibrium turbulent boundary layers under favourable pressure gradient are studied. The numerical simulations of equilibrium sink flow TBL are validated against the experimental results of Dixit (2010). A study of two-point correlations reveals that the near-wall structure angle decreases with a favourable pressure gradient in sink flow TBLs. In the outer region, the loss of streamwise coherence occurs at a wall-normal location closer to the wall than in an ZPG TBL. Edge intermittency study reveals that… Advisors/Committee Members: Ramesh, O N.

Subjects/Keywords: Fluid Dynamics; Turbulent Boundary Layer; Boundary Layer; Turbulence; Zero-Pressure-Gradient Turbulent Boundary Layer (ZPG TBL); Sink Flow Boundary Layer; Relaminarising Turbulent Boundary Layer; Equilibrium Turbulent Boundary Layer; Turbulent Boundary Layer - Numerical Simulation; Aerospace Engineeing (AE)

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Patwardhan, S. S. (2015). Effect of Favourable Pressure Gradient on Turbulence in Boundary Layers. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/2005/3831 ; http://etd.iisc.ernet.in/abstracts/4703/G26983-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Patwardhan, Saurabh Sudhir. “Effect of Favourable Pressure Gradient on Turbulence in Boundary Layers.” 2015. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/2005/3831 ; http://etd.iisc.ernet.in/abstracts/4703/G26983-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Patwardhan, Saurabh Sudhir. “Effect of Favourable Pressure Gradient on Turbulence in Boundary Layers.” 2015. Web. 12 Dec 2019.

Vancouver:

Patwardhan SS. Effect of Favourable Pressure Gradient on Turbulence in Boundary Layers. [Internet] [Thesis]. Indian Institute of Science; 2015. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/2005/3831 ; http://etd.iisc.ernet.in/abstracts/4703/G26983-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Patwardhan SS. Effect of Favourable Pressure Gradient on Turbulence in Boundary Layers. [Thesis]. Indian Institute of Science; 2015. Available from: http://etd.iisc.ernet.in/2005/3831 ; http://etd.iisc.ernet.in/abstracts/4703/G26983-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

7. Malik, Bijoy Kumar. Study of Non-Equilibrium Flow Behind Normal Shock.

Degree: 2014, Indian Institute of Science

URL: http://hdl.handle.net/2005/2891

► Normal shock problems in high enthalpy flows are of special interests to aerodynamicists and fluid dynamicists. When the shock Mach number become hypersonic and increasing… (more)

▼ Normal shock problems in high enthalpy flows are of special interests to aerodynamicists and fluid dynamicists. When the shock Mach number become hypersonic and increasing further, the gas passing through the shock is compressed resulting in increase in temperature and pressure. As the Mach number increases the internal degrees of freedom of the diatomic molecules are activated to an increasing extent when it crosses the shock resulting dissociation especially for high enthalpy flows. Hence dissociation of diatomic molecules must be taken into account in the determination of some of the aerodynamic parameters. This thermal and chemical process can be divided into three types such as nearly frozen, non-equilibrium and nearly non-equilibrium depending on the rates of reaction and excitation. For typical re-entry conditions of spacecrafts into a planets atmosphere, dissociation reactions of the molecules is dominant in the stagnation flow. Further in the stagnation region of the flow field one of the most important parameter that characterizes the flow field is the shock stand-off distance. This parameter is often employed for validation purposes of numerical methods as well as for non-reactive and reactive gases. For high Mach number flows the shock is very close to the body hence experimental determination of shock stand-off distance is very difficult and there would be relatively large errors. Therefore the theoretical determination of this parameter is of great significance in the discussion of this physical phenomenon. There are some works which presents how the dissociation behind shock affects the shock stand-off distance. Thus the dissociation behind the shock is a very important process which has great impact in aerodynamic flight and design. In this present work we studied how dissociation of diatoms occur behind a normal shock. Treanor and Marrone (1962) proposed CVD(coupled vibration-dissociation) model for diatoms by assuming diatom as a harmonic oscillator with a cut-off level. But actually diatoms are not harmonic oscillator, because spectroscopic data of energy level spacing is not like harmonic oscillator. For this reason, Treanor, Rich, and Rehm(1968) used anharmonic oscillator model for diatoms to study vibrational relaxation. Taking the anharmonicity of diatom, Philip Morse(1929) gave a formula for potential energy levels for diatoms, which is known to express the experimental values quite accurately. Unlike the energy levels of the harmonic oscillator potential, which are evenly spaced , the Morse potential level spacing decreases as the energy approaches the dissociation energy and then it is continuous. So it is quite accurate to take Morse oscillator theory for diatomic dissociation instead of harmonic oscillator with a cut-off level. We have used Morse oscillator theory to derive a dissociation-recombination reaction rate equation for diatom. To derive the rate equation we have used the transition probability between different vibrational energy levels . The rate equation is numerically solved… Advisors/Committee Members: Ramesh, O N.

Subjects/Keywords: Shock Waves; Supersonic Aerodynamics; Fluid Dynamics; Non-Equilibrium Flows; Unsteady Shock; An-harmonic Oscillator Theory; Diatomic Dissociation; Oscillator Model; Shock (Mechanics); Ionization; Morse Oscillator Theory; Shock Flow; Aerospace Engineering

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Malik, B. K. (2014). Study of Non-Equilibrium Flow Behind Normal Shock. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/2891

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Malik, Bijoy Kumar. “Study of Non-Equilibrium Flow Behind Normal Shock.” 2014. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/2891.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Malik, Bijoy Kumar. “Study of Non-Equilibrium Flow Behind Normal Shock.” 2014. Web. 12 Dec 2019.

Vancouver:

Malik BK. Study of Non-Equilibrium Flow Behind Normal Shock. [Internet] [Thesis]. Indian Institute of Science; 2014. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/2891.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Malik BK. Study of Non-Equilibrium Flow Behind Normal Shock. [Thesis]. Indian Institute of Science; 2014. Available from: http://hdl.handle.net/2005/2891

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

8. Chopde, Rahul Siddharth. Low Reynolds Number Vortex Shedding In Three-dimensional Flow.

Degree: 2004, Indian Institute of Science

URL: http://hdl.handle.net/2005/1124

Subjects/Keywords: Vortex Flow; Gas Mechanics; Aerospace Engineering

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Chopde, R. S. (2004). Low Reynolds Number Vortex Shedding In Three-dimensional Flow. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1124

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Chopde, Rahul Siddharth. “Low Reynolds Number Vortex Shedding In Three-dimensional Flow.” 2004. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/1124.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Chopde, Rahul Siddharth. “Low Reynolds Number Vortex Shedding In Three-dimensional Flow.” 2004. Web. 12 Dec 2019.

Vancouver:

Chopde RS. Low Reynolds Number Vortex Shedding In Three-dimensional Flow. [Internet] [Thesis]. Indian Institute of Science; 2004. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/1124.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Chopde RS. Low Reynolds Number Vortex Shedding In Three-dimensional Flow. [Thesis]. Indian Institute of Science; 2004. Available from: http://hdl.handle.net/2005/1124

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

9. Suhas, Diwan Sourabh. Response Of A Laminar Separation Bubble To External Excitation.

Degree: 2005, Indian Institute of Science

URL: http://hdl.handle.net/2005/1472

Subjects/Keywords: Turbomachines - Fluid Dynamics; Laminar Separation Bubbles; Boundary Layer Problems; Turbulence; Excitations; Shear Layer; Aeronautics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Suhas, D. S. (2005). Response Of A Laminar Separation Bubble To External Excitation. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1472

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Suhas, Diwan Sourabh. “Response Of A Laminar Separation Bubble To External Excitation.” 2005. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/1472.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Suhas, Diwan Sourabh. “Response Of A Laminar Separation Bubble To External Excitation.” 2005. Web. 12 Dec 2019.

Vancouver:

Suhas DS. Response Of A Laminar Separation Bubble To External Excitation. [Internet] [Thesis]. Indian Institute of Science; 2005. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/1472.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Suhas DS. Response Of A Laminar Separation Bubble To External Excitation. [Thesis]. Indian Institute of Science; 2005. Available from: http://hdl.handle.net/2005/1472

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

10. Suhas, Diwan Sourabh. Response Of A Laminar Separation Bubble To External Excitation.

Degree: 2005, Indian Institute of Science

URL: http://etd.iisc.ernet.in/handle/2005/1472 ; http://etd.ncsi.iisc.ernet.in/abstracts/1892/G19017-Abs.pdf

Subjects/Keywords: Turbomachines - Fluid Dynamics; Laminar Separation Bubbles; Boundary Layer Problems; Turbulence; Excitations; Shear Layer; Aeronautics

Record Details Similar Records Cite « Share

❌

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Suhas, D. S. (2005). Response Of A Laminar Separation Bubble To External Excitation. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/1472 ; http://etd.ncsi.iisc.ernet.in/abstracts/1892/G19017-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Suhas, Diwan Sourabh. “Response Of A Laminar Separation Bubble To External Excitation.” 2005. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/handle/2005/1472 ; http://etd.ncsi.iisc.ernet.in/abstracts/1892/G19017-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Suhas, Diwan Sourabh. “Response Of A Laminar Separation Bubble To External Excitation.” 2005. Web. 12 Dec 2019.

Vancouver:

Suhas DS. Response Of A Laminar Separation Bubble To External Excitation. [Internet] [Thesis]. Indian Institute of Science; 2005. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/handle/2005/1472 ; http://etd.ncsi.iisc.ernet.in/abstracts/1892/G19017-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Suhas DS. Response Of A Laminar Separation Bubble To External Excitation. [Thesis]. Indian Institute of Science; 2005. Available from: http://etd.iisc.ernet.in/handle/2005/1472 ; http://etd.ncsi.iisc.ernet.in/abstracts/1892/G19017-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

11. Sameen, A. Stability Of Plane Channel Flow With Viscosity-Stratification.

Degree: 2004, Indian Institute of Science

URL: http://hdl.handle.net/2005/1140

Subjects/Keywords: Aerodynamics; Channel Flow; Viscosity-Stratification; Poiseuille Flow; Plane Channel Flow; Viscosity Variatlons; Viscosity Stratification; Aeronautics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Sameen, A. (2004). Stability Of Plane Channel Flow With Viscosity-Stratification. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1140

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Sameen, A. “Stability Of Plane Channel Flow With Viscosity-Stratification.” 2004. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/1140.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Sameen, A. “Stability Of Plane Channel Flow With Viscosity-Stratification.” 2004. Web. 12 Dec 2019.

Vancouver:

Sameen A. Stability Of Plane Channel Flow With Viscosity-Stratification. [Internet] [Thesis]. Indian Institute of Science; 2004. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/1140.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Sameen A. Stability Of Plane Channel Flow With Viscosity-Stratification. [Thesis]. Indian Institute of Science; 2004. Available from: http://hdl.handle.net/2005/1140

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

12. Rajan Kuamr, *. Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack.

Degree: 2005, Indian Institute of Science

URL: http://hdl.handle.net/2005/1475

Subjects/Keywords: Subsonic Aerodynamics; Force Control; Fightercraft - High Angles of Attack; Noses (Aircraft); Nose Blunting; Nose Blowing; Slender Cone Models; Aeronautics

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❌

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Rajan Kuamr, *. (2005). Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1475

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Rajan Kuamr, *. “Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack.” 2005. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://hdl.handle.net/2005/1475.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Rajan Kuamr, *. “Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack.” 2005. Web. 12 Dec 2019.

Vancouver:

Rajan Kuamr *. Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack. [Internet] [Thesis]. Indian Institute of Science; 2005. [cited 2019 Dec 12]. Available from: http://hdl.handle.net/2005/1475.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Rajan Kuamr *. Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack. [Thesis]. Indian Institute of Science; 2005. Available from: http://hdl.handle.net/2005/1475

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

13. Sameen, A. Stability Of Plane Channel Flow With Viscosity-Stratification.

Degree: 2004, Indian Institute of Science

URL: http://etd.iisc.ernet.in/handle/2005/1140 ; http://etd.ncsi.iisc.ernet.in/abstracts/1494/G18934-Abs.pdf

Subjects/Keywords: Aerodynamics; Channel Flow; Viscosity-Stratification; Poiseuille Flow; Plane Channel Flow; Viscosity Variatlons; Viscosity Stratification; Aeronautics

Record Details Similar Records Cite « Share

❌

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Sameen, A. (2004). Stability Of Plane Channel Flow With Viscosity-Stratification. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/1140 ; http://etd.ncsi.iisc.ernet.in/abstracts/1494/G18934-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Sameen, A. “Stability Of Plane Channel Flow With Viscosity-Stratification.” 2004. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/handle/2005/1140 ; http://etd.ncsi.iisc.ernet.in/abstracts/1494/G18934-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Sameen, A. “Stability Of Plane Channel Flow With Viscosity-Stratification.” 2004. Web. 12 Dec 2019.

Vancouver:

Sameen A. Stability Of Plane Channel Flow With Viscosity-Stratification. [Internet] [Thesis]. Indian Institute of Science; 2004. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/handle/2005/1140 ; http://etd.ncsi.iisc.ernet.in/abstracts/1494/G18934-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Sameen A. Stability Of Plane Channel Flow With Viscosity-Stratification. [Thesis]. Indian Institute of Science; 2004. Available from: http://etd.iisc.ernet.in/handle/2005/1140 ; http://etd.ncsi.iisc.ernet.in/abstracts/1494/G18934-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

14. Rajan Kuamr, *. Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack.

Degree: 2005, Indian Institute of Science

URL: http://etd.iisc.ernet.in/handle/2005/1475 ; http://etd.ncsi.iisc.ernet.in/abstracts/1895/G19169-Abs.pdf

Subjects/Keywords: Subsonic Aerodynamics; Force Control; Fightercraft - High Angles of Attack; Noses (Aircraft); Nose Blunting; Nose Blowing; Slender Cone Models; Aeronautics

Record Details Similar Records Cite « Share

❌

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Rajan Kuamr, *. (2005). Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/1475 ; http://etd.ncsi.iisc.ernet.in/abstracts/1895/G19169-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Rajan Kuamr, *. “Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack.” 2005. Thesis, Indian Institute of Science. Accessed December 12, 2019. http://etd.iisc.ernet.in/handle/2005/1475 ; http://etd.ncsi.iisc.ernet.in/abstracts/1895/G19169-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Rajan Kuamr, *. “Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack.” 2005. Web. 12 Dec 2019.

Vancouver:

Rajan Kuamr *. Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack. [Internet] [Thesis]. Indian Institute of Science; 2005. [cited 2019 Dec 12]. Available from: http://etd.iisc.ernet.in/handle/2005/1475 ; http://etd.ncsi.iisc.ernet.in/abstracts/1895/G19169-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Rajan Kuamr *. Experimental Study Of Side Force Control On Slender Cones At High Angles Of Attack. [Thesis]. Indian Institute of Science; 2005. Available from: http://etd.iisc.ernet.in/handle/2005/1475 ; http://etd.ncsi.iisc.ernet.in/abstracts/1895/G19169-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

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