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X-WR-CALDESC:Events for Department of Aerospace Engineering
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TZID:Asia/Kolkata
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TZOFFSETFROM:+0530
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DTSTART:20260101T000000
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260901T110000
DTEND;TZID=Asia/Kolkata:20260901T130000
DTSTAMP:20261031T050154
CREATED:20260831T045301Z
LAST-MODIFIED:20260904T050250Z
UID:10000148-1788260400-1788267600@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg):Effect of rotation on the flow organisation and instability of a slender spinning body across quiescent\, axial and compressible regimes
DESCRIPTION:A body of revolution spinning in a fluid drives an inherently three-dimensional boundary layer\, in which a centrifugally driven secondary circulation lifts the layer off the surface and a centrifugal instability carries it into transition. Most of what is known about this flow comes from single geometries (the rotating disk\, the isolated cone or cylinder) in an unbounded fluid\, and from diagnostics that resolve neither the secondary meridional circulation nor the three-component velocity of the vortices. This work instead resolves the rotation-driven layer with whole-field measurements on a composite\, finite cone–cylinder (half-cone angle 15°)\, and follows it across the settings in which such a layer arises in practice\, of relevance to spin-stabilised flight and rotating machinery: a still fluid with and without confining walls\, the transient establishment from rest\, an imposed axial stream\, and\, as a bounding case\, a compressible free stream.\nCombining planar (two-component) and time-resolved stereoscopic (three-component) particle image velocimetry in the meridional plane with a phase-locked acquisition and a proper-orthogonal decomposition of the fluctuating field\, the study shows how confinement changes the transition from a sharp two-branch switch to a smooth downstream migration coupled to a growing separation bubble; how the layer establishes advectively from rest in a single turnover\, some fifty times faster than viscous diffusion; and how the base rotation ratio Sᵇ = ωR/U∞ organises transition under axial inflow\, with onset at Sᵇ of order unity. As a bounding case\, a slender cone spun in a Mach 2 stream leaves the shock-dominated mean flow and the surface topology essentially unchanged\, adding only broadband unsteadiness with no tonal lock-in\, so that the rotation-driven layer\, though real\, is masked at supersonic speed. Taken together\, the studies trace a single rotation-driven\, centrifugally unstable boundary layer\, with its meridional lift-up and counter-rotating vortices\, reshaped in turn by confinement\, start-up\, axial inflow and compressibility. \nSpeaker : Rajkamal Sah \nResearch Supervisor : Prof. Gopalan Jagadeesh
URL:https://aero.iisc.ac.in/event/ph-d-enggeffect-of-rotation-on-the-flow-organisation-and-instability-of-a-slender-spinning-body-across-quiescent-axial-and-compressible-regimes/
LOCATION:STC Seminar Hall\, Dept. of Aerospace Engineering
CATEGORIES:AE Seminar
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2026/09/Rajkamal-Sah.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260901T140000
DTEND;TZID=Asia/Kolkata:20260901T170000
DTSTAMP:20261031T050154
CREATED:20260825T054145Z
LAST-MODIFIED:20260825T054307Z
UID:10000147-1788271200-1788282000@aero.iisc.ac.in
SUMMARY:Taming Turbulence
DESCRIPTION:Turbulence remains one of the outstanding problems of classical physics\, and one that has challenged physicists and engineers alike for decades\, even centuries. The fusion of classical approaches and tools of the modern day – theoretical analysis of the Navier-Stokes equations\, state-of-the-art experimental observations\, data-driven methods and machine learning – has led to substantial progress towards understanding the mechanisms sustaining turbulence\, developing predictive capabilities and achieving the potentially revolutionary goal of harnessing or taming turbulence in large-scale (high Reynolds number) practical settings. In this talk\, I will describe some fundamental challenges posed by turbulence near walls\, the impact of this phenomenon on many of the world’s pressing scientific concerns\, and some recent advances.\n\n \nSpeaker : Prof. Beverley McKeon\n\nbiography:\n\nBeverley J. McKeon is Professor of Mechanical Engineering at Stanford. She received her B.A.\, M.A. and M.Eng. from the University of Cambridge in the United Kingdom\, and an M.A. and Ph.D. in Mechanical and Aerospace Engineering from Princeton University. She completed postdoctoral research and a Royal Society Dorothy Hodgkin Fellowship at Imperial College London. Best known for her work pioneering resolvent analysis as an equation-driven tool to analyze and predict the dynamics of turbulent flow\, her research group has specialized in addressing its application to understand and modify wall turbulence in numerical data and via experiments with external forcing. Prof. McKeon is a Fellow of the APS and the AIAA and the recipient of a Vannevar Bush Faculty Fellowship from the DoD in 2017\, the Presidential Early Career Award (PECASE) in 2009 and an NSF CAREER Award in 2008 as well as Caltech’s Shair Program Diversity Award\, Graduate Student Council Excellence in Mentoring Award and Northrop Grumman Prize for Excellence in Teaching. She currently serves as co-Lead Editor of Physical Review Fluids and on the editorial board of the Annual Review of Fluid Mechanics.\n \nCoffee/tea will be served after the seminar at 3:30 pm.\n\nAt 4:00 pm\, Prof. McKeon will hold a special session on Physical Review Fluids\, one of the world’s leading research journals for fluid dynamics. Prof. McKeon is the co-Lead Editor of the journal. The session includes a short presentation on the journal’s history\, Q&A\, and a short tutorial on writing a successful submission.
URL:https://aero.iisc.ac.in/event/taming-turbulence/
LOCATION:Auditorium (AE 005)\, Department of Aerospace Engineering
CATEGORIES:AE Seminar
ATTACH;FMTTYPE=image/png:https://aero.iisc.ac.in/wp-content/uploads/2026/08/taming_turbulence_poster_16x9-4.png
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260915T110000
DTEND;TZID=Asia/Kolkata:20260915T130000
DTSTAMP:20261031T050154
CREATED:20260909T051218Z
LAST-MODIFIED:20260915T051721Z
UID:10000149-1789470000-1789477200@aero.iisc.ac.in
SUMMARY:Invited Talk on the Occasion of the Engineer's Day - From MV to Spaceflight: Satellite Re-entry and the Future of Space Sustainability
DESCRIPTION:National Engineers’ Day commemorates the legacy of Sir M. Visvesvaraya\, whose vision and engineering leadership helped lay foundations for India’s technological development. From civil infrastructure and water resource management to advanced aerospace systems\, India’s engineering journey has been characterised by the pursuit of innovation that delivers enduring societal value. As India extends its capabilities in space exploration\, satellite services\, human spaceflight\, and a growing commercial space sector\, attention is increasingly turning to the sustainability of space activities across the entire lifecycle of a spacecraft\, including its final return to Earth.\nThis seminar examines the end-of-life phase of satellites\, focusing on the competing concepts of design for demise and design for recovery during atmospheric re-entry. While these approaches have traditionally been evaluated in terms of ground safety and debris mitigation\, recent studies have raised important questions regarding the introduction of metallic oxides and other compounds into atmospheric regions where they are not normally present. Drawing on observations of spacecraft re-entries and current research into demise physics\, material response\, and environmental impacts\, the presentation will explore the challenges and opportunities associated with sustainable spacecraft disposal. In doing so\, it considers how future spacecraft design and operations may contribute to a responsible and enduring spacefaring future for India and the global community. \nSpeaker : Prof. David Buttsworth \nBiography ::\nProfessor David Buttsworth is Professor of Thermofluids Engineering at the University of Southern Queensland\, where he leads the Hypersonics and Rocketry Group within the Institute for Space\, Defence and Advanced Technologies. He is also an Honorary Professor at the University of Queensland\, from which he holds a BE (Hons) and a PhD on shock-induced mixing and combustion in scramjets. He designed and built the TUSQ hypersonic wind tunnel\, a key Australian facility for re-entry and hypersonic ground testing\, and has led airborne optical observation campaigns of spacecraft re-entry\, including the Hayabusa capsule return. He currently leads Australian Research Council-funded research on the dispersion and demise of spacecraft components during atmospheric re-entry. He is a Senior Member of the American Institute of Aeronautics and Astronautics. Prof. Buttsworth is a Fellow of the Society for Shock Wave Research
URL:https://aero.iisc.ac.in/event/invited-talk-on-the-occasion-of-the-engineers-day-from-mv-to-spaceflight-satellite-re-entry-and-the-future-of-space-sustainability/
LOCATION:Auditorium (AE 005)\, Department of Aerospace Engineering
ATTACH;FMTTYPE=image/png:https://aero.iisc.ac.in/wp-content/uploads/2026/09/Slide1.png
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260921T110000
DTEND;TZID=Asia/Kolkata:20260921T130000
DTSTAMP:20261031T050154
CREATED:20260917T113043Z
LAST-MODIFIED:20260923T090942Z
UID:10000151-1789988400-1789995600@aero.iisc.ac.in
SUMMARY:Illuminating Complex Flows: Optical Diagnostics for Aerospace Applications
DESCRIPTION:Hypersonic flight represents a major frontier in aerospace engineering\, with its realization requiring a fundamental understanding of coupled chemical and fluid dynamic processes across multiple environments. Of particular importance are the reacting flows within the propulsion systems that enable sustained hypersonic flight and the high-temperature\, chemically reacting flows that develop near vehicle surfaces at extreme speeds. Understanding the complex and strongly coupled phenomena governing these environments requires a synergistic combination of high-fidelity computation and carefully designed experiments. Experimental investigations\, however\, are inherently challenging\, often relying on sophisticated ground-based facilities equipped with advanced diagnostic capabilities to generate meaningful\, high-resolution data. Among these\, optical diagnostics have emerged as a powerful class of measurement tools\, offering significant advantages over conventional techniques. Their non-intrusive nature\, high temporal resolution\, and robustness under extreme conditions make them uniquely suited for probing high-speed\, high-enthalpy flows. Continued advances in optical diagnostics have enabled transformative progress across multiple domains of aerospace research\, including chemical kinetics\, aerodynamics\, and active flow control.\nThis talk will focus on a specific application of advanced optical diagnostics: elucidating the chemical kinetics of complex fuels such as jet fuels\, gasoline surrogates\, and rocket propellants under engine-relevant conditions. Particular emphasis will be placed on the role of advanced laser-based diagnostics\, coupled with shock tube reactors\, in uncovering fundamental insights into the behavior of large hydrocarbons and their mixtures at elevated temperatures and pressures. These insights have enabled the development of the Low-Temperature Hybrid Chemistry (LT-HyChem) framework\, a methodology for constructing compact\, fuel-specific chemical kinetic models that remain valid across the full range of operating conditions relevant to modern and next-generation propulsion systems. The LT-HyChem approach is fuel-agnostic and produces models that are over two orders of magnitude more compact than those generated using conventional methodologies\, while simultaneously reducing predictive uncertainties by more than an order of magnitude. This combination of compactness and accuracy facilitates integration with computational fluid dynamics solvers\, significantly reducing the computational cost associated with combustor design\, analysis\, and optimization. The talk will conclude with a discussion of the broader implications of this work for rapid screening of sustainable aviation fuels and potential extensions to solid fuel systems.\n\nSpeaker: Dr. Rishav Choudhary\n\nBiography:\nDr. Rishav Choudhary received his B.Tech. in Aerospace Engineering from IIT Kanpur and his M.S. and Ph.D. in Mechanical Engineering from Stanford University. His doctoral research focused on absorption-spectroscopy-based diagnostics for chemical kinetics under extreme conditions relevant to engine combustion\, hypersonic re-entry\, and other high-temperature environments. He subsequently worked as a Postdoctoral Researcher in Aerospace Engineering at the University of Michigan\, developing optical diagnostics for high-speed density fluctuations\, velocity measurements in supersonic flows\, and electron-density measurements in plasmas. He is currently an Engineer at Lam Research Corporation\, where his work involves optical diagnostics applied to multiphase flows and plasmas relevant to semiconductor manufacturing.\n\nNote: Dr. Rishav Choudhary is a faculty candidate in the Propulsion stream in the Department of Aerospace Engineering\, IISc. Faculty members are encouraged to attend the talk and interact with the candidate.\n\n\n\n\n\n 
URL:https://aero.iisc.ac.in/event/illuminating-complex-flows-optical-diagnostics-for-aerospace-applications/
LOCATION:Auditorium (AE 005)\, Department of Aerospace Engineering
CATEGORIES:AE Seminar
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2026/09/Dr.-Rishav-.jpg
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260922T103000
DTEND;TZID=Asia/Kolkata:20260922T123000
DTSTAMP:20261031T050154
CREATED:20260921T133040Z
LAST-MODIFIED:20260923T094114Z
UID:10000152-1790073000-1790080200@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Development of Learning-based Strategies for Reconnaissance with Multi-Robot Systems
DESCRIPTION:Reconnaissance is the contest for information about a territory: one side tries to observe an asset or a guarded area\, the other tries to deny it. Low-cost drones have made this contest cheap and constant\, and protecting critical infrastructure against it is now a crucial problem\, because an intruder no longer needs to strike a target to threaten it. This thesis develops learning-based strategies for multi-robot reconnaissance from both of its perspectives. In the defense perspective\, a team of defenders must deny reconnaissance of a protected territory by intercepting intruders before they cross its perimeter. In the adversarial perspective\, an agent inside a guarded region must escape to a safe area with the information it has gathered before it is neutralized. Both are hard for the same real-world reasons: opponents arrive from any direction at any time\, so the environment is non-stationary; each robot senses only a limited range\, so the state is partially observed; communication may be unavailable; and the opponent’s numbers and strategy are unknown. Classical game-theoretic and assignment-based methods assume away one or more of these conditions\, which motivates strategies that learn from local observations.\nFor the defense perspective\, the thesis first formulates perimeter defense as a decentralized assignment learning problem and develops the Context-aware Deep Assignment Network (CDAN). Each defender encodes its limited field of view as a spatio-temporal context map of past observations\, the present\, and a predicted future with position uncertainty; pseudo-values around each intruder counter the sparsity of this map and allow a 3D convolutional network\, trained by imitating a centralized solution\, to converge and to be reused by the whole team. CDAN captures about 6% more intruders than the best decentralized baseline (73.4% against 67.5%) and generalizes over team size\, perimeter length\, and intruder speed and maneuvers. Because assignment quality inherits the reliability of the communication channel\, the second contribution\, CARE (Communication-free planning using Adaptive Regions of Engagement)\, resolves the assignment from each defender’s own observations: a defender senses over its full detection radius but commits only within an engagement region set by the distance to its nearest observed teammate\, and drifts its rest position toward the arrival directions it has itself observed. Without a single message\, CARE matches or exceeds communicating baselines over about 200 scenarios and 38\,600 seed-paired episodes\, and is demonstrated on a Crazyflie quadrotor team.\nFor the adversarial perspective\, the third contribution gives the first reinforcement learning formulation of the confinement escape problem\, with a constant-size LiDAR-based state that is independent of the number of pursuers and the shape of the region\, and proposes Scaffolding Reflection based Reinforcement Learning (SR2L)\, in which a simple motion-planner scaffold guides the learner only when its suggestion is clearly better\, so that it can accelerate learning but never damage it. SR2L converges in about half the episodes of standalone actor-critic methods and escapes faster against three pursuit strategies\, with the lowest variance in every case.\nBecause no single learned policy is best under all conditions\, the fourth contribution fuses a pool of pre-trained policies online in a non-stationary environment. Standard multiplicative-weights fusion collapses onto one policy and performs worse than doing nothing. Regularized Reward-aware Online LEarning (ROLE) adapts the fusion weights from the reward of the executed action alone\, without ground truth\, and bounds every weight with an anti-collapse cap. ROLE raises perfect escape runs from 41% for the best single policy to 68% on healthy pools and degrades gracefully when rogue policies contaminate the pool.\nTogether\, these contributions treat reconnaissance in multi-robot systems as one problem seen from two perspectives\, and show that learning from local observations\, with minimal or no information exchange\, can both deny reconnaissance of a protected territory and accomplish it from inside a guarded one. \nSpeaker : Vignesh Gurumurthy \nResearch Supervisor: Prof. Suresh Sundaram \n 
URL:https://aero.iisc.ac.in/event/ph-d-engg-development-of-learning-based-strategies-for-reconnaissance-with-multi-robot-systems/
LOCATION:STC Seminar Hall\, Dept. of Aerospace Engineering
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2026/09/Vignesh-Gurumurthy.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260925T150000
DTEND;TZID=Asia/Kolkata:20260925T170000
DTSTAMP:20261031T050154
CREATED:20260915T052755Z
LAST-MODIFIED:20260915T052755Z
UID:10000150-1790348400-1790355600@aero.iisc.ac.in
SUMMARY:Magneto-Active Solids for Adaptive Structures: Can Magnetic Fields Control Elastic Waves?
DESCRIPTION:Magneto-active solids couple their mechanical response to externally applied magnetic fields\, providing a promising route toward remotely tunable materials and structures. Such functionality is particularly attractive for aerospace applications involving vibration isolation\, adaptive structures\, sensing\, and elastic-wave control. However\, exploiting this coupling requires understanding a fundamental question: when does a magnetic field actually modify elastic-wave propagation\, and which wave modes are affected?\n\nIn this seminar\, Prof. Galich will present recent theoretical and experimental work on elastic waves in magneto-active solids. Starting from the incremental theory of nonlinear magnetoelasticity\, he will introduce the generalized acoustic tensor governing small-amplitude waves superimposed on a magnetically biased state. For compressible isotropic magneto-active polymers\, magnetic tunability is shown to be strongly dependent on wave polarization. In an undeformed material subjected to a magnetic field transverse to the propagation direction\, the shear wave polarized along the magnetic field is directly field-sensitive\, whereas the pressure wave and the orthogonally polarized shear wave remain essentially unaffected. These theoretical predictions are supported by ultrasonic experiments on 3D-printed iron-filled polymers.\n\nThe discussion will then extend from bulk waves to Rayleigh surface waves\, where the coupling between mechanics and magnetism introduces additional questions concerning constitutive modeling and stability. In particular\, physically consistent selection of magnetoelastic material parameters is essential: models that reproduce the magnetic permeability but violate the corresponding Maxwell-stress condition can predict artificially strong wave-speed changes and even surface instabilities.\n\nFinally\, the seminar will cover periodic magneto-active solids\, where magnetic fields\, finite deformation\, and material architecture can be combined to control elastic-wave dispersion and phononic bandgaps. These results illustrate both the opportunities and fundamental limitations of magnetic-field control of elastic waves and provide guidelines for the development of adaptive materials and structures for vibration manipulation.\n\nSpeaker :  Prof. Pavel I. Galich\n\nBiography:\n\nProf. Pavel I. Galich has been an Assistant Professor at The Stephen B. Klein Faculty of Aerospace Engineering\, Technion\, since 2020. He earned his Ph.D. in Aerospace Engineering from the Technion in 2018 and served as a Postdoctoral Research Associate in the Department of Materials Science & NanoEngineering (MSNE) at Rice University from 2018 to 2020.
URL:https://aero.iisc.ac.in/event/magneto-active-solids-for-adaptive-structures-can-magnetic-fields-control-elastic-waves/
CATEGORIES:AE Seminar
ATTACH;FMTTYPE=image/png:https://aero.iisc.ac.in/wp-content/uploads/2026/09/Prof.-Pavel-I.-Galich.png
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20260926T160000
DTEND;TZID=Asia/Kolkata:20260926T170000
DTSTAMP:20261031T050154
CREATED:20260923T060556Z
LAST-MODIFIED:20260923T102930Z
UID:10000153-1790438400-1790442000@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): A Slotted Wing Configuration for STOL Applications
DESCRIPTION:The rapid development of Urban Air Mobility (UAM) has led to the emergence of electric vertical take-off and landing (eVTOL) aircraft\, with many current concepts relying on tilt-rotor or other complex propulsion-conversion mechanisms to achieve vertical take-off and landing followed by efficient forward flight. While these configurations provide the required operational flexibility\, the mechanical complexity associated with tilting propulsion systems can introduce challenges related to durability\, power efficiency\, system integration\, and flight stability. This thesis explores an alternative approach based on short take-off and landing (STOL) capability\, with the objective of developing a compact\, mechanically simple\, and aerodynamically efficient wing configuration that can reduce the dependence on such complex mechanisms. The proposed design is CFD based and the required computations have been carried out using the CFD solver HiFUN. All computations have been performed using standard SA turbulence model. The propellers are simulated using varying levels of fidelity available in the solver\, such as the Blade Element Method and sliding mesh simulations. Moving mesh capability available in the solver is made use of in simulating synthetic jets.\nA novel fixed-wing configuration is developed specifically for STOL operation in the context of urban air mobility. Instead of relying on conventional high-lift devices\, the proposed configuration combines a highly cambered wing\, distributed propulsion\, and active flow control to achieve the high lift required during take-off and landing. A NACA four-digit formulation is used to define the airfoil\, with an unconventionally high camber and a slot introduced at the location of maximum camber. To maintain vehicle compactness while improving aerodynamic efficiency\, a low aspect-ratio wing with optimized end plates is employed. The influence of end-plate size on the aerodynamic performance is investigated\, showing a progressive reduction in trailing-vortex strength and associated induced effects on lift and drag with increasing end-plate size. Based on the investigated configurations\, an end plate with a width equal to 20% of the wing aerodynamic chord is selected.\nDistributed propulsion is subsequently integrated into the wing configuration to exploit propeller slipstream effects during STOL operation. An enhanced actuator-disc model\, coupled with blade-element analysis\, is used to represent the propellers\, with a NACA 640 four-bladed propeller selected for the study. The propeller thrust requirements are determined from the take-off drag of the unpowered wing and distributed among four equally spaced propellers. The interaction between an individual propeller and the wing is first investigated to determine the optimum propeller location. The resulting slipstream–wing interaction substantially increases the wing lift\, thereby reducing the required take-off velocity. The complete powered configuration is then investigated using high-fidelity sliding-mesh simulations with counter-rotating propellers arranged on either side of the wing. \nThe high camber required to achieve the desired lift characteristics introduces a separation bubble in the rear portion of the wing downstream of the slot. To address this limitation without introducing conventional high-lift mechanisms\, a zero-net-mass-flux active flow-control system based on synthetic jets is incorporated. A dynamic-mesh methodology is first validated against the NASA Langley Research Center standard hump test case with oscillatory control. The validated methodology is then used to establish the actuator momentum coefficient and excitation frequency. To reduce the computational cost of the full-wing simulations\, an unsteady boundary-condition model is developed and validated and subsequently employed to investigate the effectiveness of synthetic-jet actuation in suppressing the separation bubble and improving the aerodynamic performance of the wing. Discrete synthetic-jet slits are positioned between the propeller slipstreams\, allowing flow control to be concentrated in regions outside the primary propeller wakes while reducing the additional power requirement.\nOverall\, the thesis demonstrates the feasibility of combining fixed-wing STOL aerodynamics\, distributed propulsion\, and localized active flow control as an alternative pathway for compact urban air-mobility vehicles. \n  \nSpeaker : S Amsha \nResearch Supervisor : N. Balakrishnan
URL:https://aero.iisc.ac.in/event/ph-d-engg-a-slotted-wing-configuration-for-stol-applications/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2026/09/S-Amsha.jpg
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