BEGIN:VCALENDAR VERSION:2.0 PRODID:-//wp-events-plugin.com//6.5.2//EN TZID:Asia/Kolkata X-WR-TIMEZONE:Asia/Kolkata BEGIN:VEVENT UID:8@aero.iisc.ac.in DTSTART:20240313T140000Z DTEND:20240313T150000Z DTSTAMP:20240322T042526Z URL:https://aero.iisc.ac.in/events/test-event/ SUMMARY:Thesis Colloquium DESCRIPTION:\n\n\n\n\n\n\nAsymptotic Modelling of Carbon Nanotube (CNT) and CNT-reinforced composite structures using strain gradient formulations\n& nbsp\;\n\n\nResearch Supervisor: Dineshkumar Harursampath\n\nThesis Abstra ct\n\nCarbon nanotubes (CNTs) have garnered attention for their remarkable mechanical\, thermal\, and electrical properties\, making them valuable i n various applications. CNTs are particularly advantageous in aerospace st ructures as reinforcements in polymer matrix composites\, enhancing struct ural strength while reducing weight. Furthermore\, they offer the potentia l for multifunctionality\, integrating structural\, thermal\, and electric al functionalities within components like wings. However\, accurately mode lling CNT behaviour poses challenges\, especially considering their applic ation in larger-scale aerospace structures. While accurate\, molecular dyn amics and molecular structural mechanics are computationally intensive and limited in length scale. In this context\, the present research proposes reduced-order continuum structural models using the Variational Asymptotic Method (VAM) to study CNT and its composite structures while incorporatin g length scale effects using strain-gradient formulations.\n\nUsing VAM\, single-walled CNTs (SWCNTs) were first analysed by considering them as str aight\, hollow\, circular tubes in a local continuum framework. This tube model accounts for the geometrically nonlinear behaviour of standalone CNT when subjected to bending and buckling loads. Cross-sectional ovalisation leading to nonlinear bending and buckling behaviour has been studied. Com bined loading cases of bending and compression and torsion and compression and bending and torsion have been examined. The study aims to provide ins ights into the 3-D nonlinear deformation behaviour of SWCNTs\, offering a more efficient approach for evaluating CNTs in aerospace composite applica tions.\n\nIn the next step\, recognising the significance of the structure 's small size (such as used in MEMS\, NEMS\, and sensors)\, the non-classi cal theories\, such as the Modified Strain Gradient Theory\, which account for the size effect in the material\, have been employed to develop a pio neering beam and plate models tailored for CNT-reinforced composite struct ures. Emphasising the critical nature of size effects\, characterised by l ength scale parameters\, this study delves into the nuances of the length scale effects in nanoscale structures. To develop the asymptotically-corre ct strain-gradient beam model\, a prismatic beam with a rectangular cross section has been considered to derive zeroth-order and subsequent higher-o rder models while capturing the strain-gradient effects. Notably\, this wo rk is the first application of non-classical theories in developing VAM-ba sed beam models. Different orders for length scale parameters have been co nsidered\, and the validity of each choice is scrutinised\, followed by gu idance on the appropriate choice of the length scale parameters.\n\nFollow ing the development of the strain-gradient beam model\, a modified strain gradient theory-based plate model has also been developed using VAM\, whic h is again a first-of-its-kind work in the context of VAM and reduced-orde r structural models. Using the variational methods\, fourth-order ordinary differential equations were obtained for the non-classical case\, and sim ilarly\, an additional set of boundary conditions (non-classical) were als o derived. The warping solutions and the plate stiffnesses are obtained by solving these governing differential equations and boundary conditions. I t was noted that the material length scale parameters appear only in the b ending and twist stiffness terms. Further\, the classical results can be d erived by setting the material length scale parameters as zero. Zeroth- an d first-order approximations have been derived\, followed by detailed vali dation of the results with literature for bending and buckling load cases. Parametric studies involving variations in thickness and plate width have been conducted to assess their influence on mechanical behaviour. The dev eloped plate model is then applied to CNT-reinforced composites\, and thei r bending and buckling studies have been carried out. The parametric studi es have also considered evaluating all influencing parameters like CNT vol ume fraction\, material length scale parameter\, plate thickness and width .\n\nFull Meeting Link: https://teams.microsoft.com/l/meetup-join/19%3ame eting_ZWY1NmM0MGItODQ5ZS00ZmE4LTk5YjMtYWMyMGQ3ZGE1ODlh%40thread.v2/0?conte xt=%7b%22Tid%22%3a%226f15cd97-f6a7-41e3-b2c5-ad4193976476%22%2c%22Oid%22%3 a%22eb59112f-967f-4f24-8739-385858c5592e%22%7d\n\n\n\nVenue: STC Seminar H all\, 1st Floor\, Dept of Aerospace Engineering\n\n\n\n\n\n\n CATEGORIES:Thesis Colloquium END:VEVENT BEGIN:VEVENT UID:10@aero.iisc.ac.in DTSTART:20240304T143000Z DTEND:20240304T160000Z DTSTAMP:20240324T071655Z URL:https://aero.iisc.ac.in/events/nonequilibrium-reacting-flows/ SUMMARY:AE Seminar DESCRIPTION:Nonequilibrium reacting flows: First principles based modeling for chemical kinetics and hydrodynamics\n\nSpeaker\nDr. Narendra Singh\nPo stdoc Research Associate\, Standford University\n\nAbstract\nPredicting st ate of the gas hitting vehicles flying at hypersonic speeds (Mach ~5) is c hallenging and is an exciting area of research. Hypersonic flows create sh ock waves\, which compress and heat the surrounding gas to high-temperatur es\, nearly thousands of Kelvins. At these high temperatures\, air molecul es (nitrogen and oxygen) dissociate into atomic species. Predicting the ex tent of dissociation and recombination of atomic species is important sinc e the state of the gas near the vehicle surface determines heating rates a nd gas-surface chemistry that damages the heat shield. Since experiments i n ground test facilities do not mimic such extreme flight conditions\, num erical simulation plays an important role. Predictive numerical simulation s require accurate reaction chemistry models. Computational models develop ed thus far range from simple empirical models fit to limited experimental data to models with millions of input parameters that track individual qu antized energy state transitions. The level of model fidelity required for accurate engineering analysis remains an open question of active researc h. Models coupling internal energy and dissociation chemistry tend to be d eveloped at either the kinetic scale or the continuum scale. In this work\ , we develop new nonequilibrium models for shock heated flows that are an alytically consistent between kinetic and continuum scales and are based o n recent ab-initio data\, applicable to large-scale CFD and direct simula tion Monte Catlo (DSMC) simulations.\n\nNonequilibrium Hydrodynamics: The Navier-Stokes equations\, typically employed even at strong non-equilibriu m conditions\, wherein thermodynamic fluxes such as stresses and heat flu x vector are based on linear irreversible thermodynamics\, not be accurate in multiscale and multiphysics scenarios encountered in hypersonic flows. Similarly\, the Navier-Stokes equations are known to breakdown in rarefie d (low density) gas flows. Therefore\, a new formalism is proposed to circ umvent these issues\, which can also benefit\, hybrid methods that can co mbine continuum description using the Navier-Stokes equations and microsco pic description\, necessary for efficient high-fidelity numerical simulati ons. Other wide range of physics problems such as nano-scale flows\, plas ma physics modeling\, and general complex gas flows can also benefit from the proposed new non-equilibrium hydrodynamic formalism.\nBrief Bio of Spe aker:\nDr. Narendra Singh graduated with a PhD (and MS) in Aerospace Engin eering (with minor in Mathematics and Chemistry) from University of Minnes ota. Narendra obtained his undergraduate degree (with Honors) in MechE fro m IIT Bombay. In his doctoral thesis\, Narendra developed chemical kinetic s models for DSMC and CFD using first principles-based approach. In additi on\, Narendra (along with Prof.Agrawal) has developed higher order equatio ns for rarefied and strong nonequilibrium flows\, known as O-13 and O-Burn ett equations\, where O ‘refers’ to Onsager due to the consistency of equations with Onsager’s reciprocity principle. Narendra Singh did his 2 years postdoc in MechE at Stanford\, where his research spanned particle- laden flows\, carbon sequestration\, and ultrafast chemistry at SLAC. Curr ently\, he is a postdoc research associate at Center for Hypersonic\, UIUC \, and developing reduced order models for chemical kinetics. ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2022/ 11/slide-3.jpg CATEGORIES:Seminar Series END:VEVENT BEGIN:VEVENT UID:9@aero.iisc.ac.in DTSTART:20240205T140000Z DTEND:20240205T150000Z DTSTAMP:20240321T084056Z URL:https://aero.iisc.ac.in/events/innovations-in-aerospace-systems/ SUMMARY:AE Seminar DESCRIPTION:Innovations in Aerospace Systems – Current Research (includin g Artificial Intelligence) and Future Challenges\n\nSpeaker\nProf. Krishna Dev Kumar\nProfessor of Aerospace Engineering\nDirector of Artificial Int elligence for Aerospace Systems Laboratory\nToronto Metropolitan Universit y\, Canada\n\nAbstract\nAircraft and spacecraft are highly complex systems \, comprising various subsystems such as flight control\, propulsion\, and power. These subsystems feature Multiple Input &\; Multiple Output (MI MO) configurations and exhibit highly nonlinear characteristics. Over rece nt years\, there has been a growing demand for aerospace systems with impr oved performance\, fault tolerance\, and enhanced autonomous capabilities. This presentation explores how fault diagnosis\, prognosis and artificial intelligence can address these requirements. It delves into model-based\, data-driven (artificial intelligence)\, and hybrid approaches\, which hav e been proposed for fault diagnosis and prognosis. Furthermore\, the autho r has proposed novel methods to meet these evolving demands. These innovat ive techniques\, including the Covariance-based adaptive unscented Kalman filter (CAUKF)\, Binary grid covariance adaptive Kalman filter (GAUKF)\, R einforced Unscented Kalman Filter (an integration of UKF and Reinforcement Learning techniques)\, and Growing Neural Networks (GNN)\, hold promise f or aerospace system enhancement. The presentation will feature case studie s illustrating the application of these methods in spacecraft attitude and orbit control systems\, as well as aircraft engines. By examining the lat est advancements and methodologies\, attendees will gain insights into the pivotal role these techniques play in enhancing aerospace system reliabil ity and efficiency\, ultimately addressing current research challenges and shaping the trajectory of future aerospace systems.\nBrief Bio of Speaker :\nDr. Krishna D. Kumar is a Professor of Aerospace Engineering and Direct or of Artificial Intelligence for Aerospace Systems (AIAS) Laboratory at T oronto Metropolitan University\, Canada. Additionally\, he is the Founder and President of iSAC Systems Inc\,  a leader in Artificial Intelligence (AI)\, Internet-of-Things (IoT)\, and Smart Systems since 2010. Prof. Kuma r has made outstanding contributions with major impact in the areas of spa cecraft dynamics and control\, fault diagnosis and prognosis\, artificial intelligence\, and predictive analytics with over 250 publications includi ng 5 books\, 14 intellectual properties\, and four patents. His AI and IoT products have been deployed across diverse industries\, including aerospa ce\, transportation\, and waste management. His illustrious career boasts several remarkable achievements\, including the development of AI-powered predictive analytics for the NASA Kepler Spacecraft and Aircraft Engines\, the world's first 100-gram miniature satellite\, and the world's first mi niature IoT monitoring systems for Bombardier Trains\, and Safran Aircraft Landing gears.  Prof. Kumar’s exemplary contributions to the field hav e been widely recognized with numerous national and international awards\, including the prestigious Canada Research Chair Award\, Ontario Early Res earcher Award\, Associate Fellow of American Aeronautics and Astronautics\ , Japan Society for the Promotion of Science Fellow\, Japan Science and Te chnology Agency Fellow\, Member of the International Academy of Astronauti cs in France\, the Sarwan Sahota Ryerson Distinguished Scholar Award\, and the Eminent Alumnus Award from Veer Surendra Sai University of Technology \, Sambalpur\, India. Furthermore\, Prof. Kumar is the Co-Editor of Acta A stronautica and Transactions of the Japan Society for Aeronautical and Sp ace Sciences.\nVenue\nSTC Seminar Hall\, Dept. of Aerospace Engineering ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2022/ 11/home-image1.jpg CATEGORIES:Seminar Series END:VEVENT BEGIN:VEVENT UID:7@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata:20191127T000000 DTEND;TZID=Asia/Kolkata:20191129T000000 DTSTAMP:20221124T122338Z URL:https://aero.iisc.ac.in/events/india-usa-lecture-series-on-aging-aircr aft-iulsaa/ SUMMARY:India - USA Lecture Series on Aging Aircraft (IULSAA) DESCRIPTION:27 – 29 November 2019\nDepartment of Aerospace Engineering\,\ nIndian Institute of Science\,\nBangalore\, India\n\n INDIA-USA LECTURE SE RIES ON AGING AIRCRAFT (IULSAA) Venue: Satish Dhawan Auditorium\, IISc\, B engaluru\, India \n\nTECHNICAL PROGRAM\n\nNovember 27\, 2019 \n\n08.00 am - 09.00 am Registration 09.00 am - 09.50 am Inaugural Session\nPlenary -Se ssion Chair:\n09.50 am - 10.20 am First Plenary Talk Sustenance of Aircraf t Fleet Through Aging Management Air Marshal Shashiker Choudhary\, Air Off icer-in-ChargeMaintenance\, Air Headquarters\, New Delhi 10.20 am - 10.50 am Second Plenary Talk Environment Effects on Aging of Structures William Nickerson\, Office of Naval Research\, Arlington\, USA 10.50 am - 11.20 am Coffee/Tea Break\n\nSession I Chair:\n11.20 am - 12.20 pm Aging Aircraft: An Introduction Dr S G Sampath\, FAA\, USA - Retired 12.20 pm - 01.20 pm Airframe and Aeroengine Fatigue under Extended Service Usage Dr R Sunder\, Bangalore Integrated System Solutions\, Bangalore 01.20 pm - 02.00 pm Lun ch\n\nSession II A Chair:\n02.00 pm - 03.00 pm NDE and SHM for Aerospace A pplications Dr Krishnan Balasubramaniam \, IIT Madras 03.00 pm - 04.00 pm Aging Aircraft Engines Dr Prakash Patnaik\, National Research Council\, Ca nada 04.00 pm - 04.15 pm Coffee/Tea Break\n\nSession II B Chair:\n04.15 pm - 05.15 pm Overview of Helicopter Fatigue Mr. Ugo Mariani\, Leonardo Heli copters\, Italy 06.00 pm - 08.00 pm Cultural Program-An Evening of Carnati c Music Carnatic Music Concert by Prof. Sankaran Mahadevan\, Vanderbilt Un iversity 08.15 pm onwards Dinner at IISc Guest House Lawns\n\nNovember 28\ , 2019 \n\nSession III A Chair:\n09.00 am - 10.00 am Corrosion Monitoring Dr Prakash Mangalgiri\, Visiting Professor\, IIT Kanpur 10.00 am - 11.00 a m Review and Assessment of Airframe Repair Schemes Dr Jayanth Kudva\, Next Gen Aeronautics\, USA 11.00 am - 11.30 am Coffee/Tea Break\n\nSession III B Chair:\n11.30 am - 12.30 pm Monitoring Aircraft Load Spectrum Towards a n Integrated Structural Health Management Prof. Afzal Suleman\, University of Victoria\, Canada 12.30 pm - 01.30 pm Lunch\n\nSession IV Chair:\n01.3 0 pm - 02.30 pm Electromagnetic NDE Activities at MSU on Aging Aircraft ND E Prof. Lalita Udpa\, Michigan State University\, USA 02.30 pm - 03.30 pm Digital Twin Technology for Aircraft Health and Operations Management unde r Uncertainty Prof. Sankaran Mahadevan\, Vanderbilt University\, USA 03.30 pm - 04.00 pm Coffee/Tea Break\n\nSession V Chair:\n04.00 pm - 05.00 pm E ffect of Newly Promulgated\, Environmental Rules Dr Prakash Patnaik\, Nati onal Research Council\, Canada 05.00 pm - 06.00 pm Aging of Aircraft Elect rical Wiring H R Sudarashan Prasad\, Centre of Excellence in Aerospace and Defence\, Bangalore 07.30pm onwards Banquet Dinner at Kirloskar Hut\, Ban galore Golf Club\, Bangalore\n\nNovember 29\, 2019 \n\nSession VI Chair:\n 09.00 am - 10.15 am Human Factors in Aircraft Maintenance and Inspection P rof. Colin Drury\, SUNY\, Buffalo\, USA 10.15 am - 11.15 am Aging Avionics Shri Yogesh Kumar\, HAL\, Bangalore - Retired 11.15 am - 11.30 am Coffee/ Tea Break\n\nSession VII Chair:\n11.30 am - 12.30 pm Technology Insertion into a Combat Aircraft: Opportunities And Challenges Dr K Vijayaraju\, Aer onautical Development Agency (DRDO) 12.30 pm - 01.30 pm Structural Life Ma nagement in a Combat Aircraft Dr A R Upadhya\, Former Director\, CSIR-NAL and Dr Mangalgiri\, Visiting Prof\, IIT\, Kanpur 01.30 pm - 02.30 pm Lunch \n\nSession VIII Chair:\n02.30 pm - 03.00 pm Presentation from DGCA 03.00 pm - 03.30 pm Presentation from Private Airlines 03.30 pm - 04.00 pm Coffe e/Tea Break 04.00 pm - 04.30 pm Feedback Session\n\nWebsite URL CATEGORIES:Conferences END:VEVENT BEGIN:VEVENT UID:6@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata:20190222T160000 DTEND;TZID=Asia/Kolkata:20190222T180000 DTSTAMP:20221124T122229Z URL:https://aero.iisc.ac.in/events/assessment-of-resolvent-analysis-as-a-t ool-for-active-flow-control-design/ SUMMARY:Assessment of resolvent analysis as a tool for active flow control design DESCRIPTION:Simon Tödtli\nGraduate Aerospace Laboratories\nCalifornia Inst itute of Technology\n\n\nReducing turbulent drag on engineering surfaces s uch as ship hulls or pipes has the potential of tremendous energetic savin gs. However\, tractable and efficient flow models for designing drag reduc tion mechanisms\, such as active feedback flow control or compliant surfac es\, are currently missing in the literature. This talk describes a flow m odel (Luhar et al\, J. Fluid Mech. 2014) based on the resolvent analysis of McKeon &\; Sharma (J. Fluid Mech. 2010) and assesses its potential for designing active feedback flow control schemes for drag reduction in i ncompressible wall-bounded flows. The assessment is based on a generalized version of the well-known opposition control scheme (Choi et al\, J Fluid Mech. 1994)\, which allows for a phase-shift between the sensor measurem ent and the actuator response. The resolvent model predicts that the phase shift strongly affects the attainable drag reduction and suggests that a range of nonzero phases offer improved control effectiveness. We validate these predictions by means of a parametric DNS study and show that the res ponse of the full nonlinear system to opposition control with various phas e shifts very closely follows the low-order model predictions. We close wi th a short discussion of the structural features of various controlled flo ws\, which provide first insights into the role of the phase in the real f low and the physics of drag reduction.\n\n CATEGORIES:Seminar Series END:VEVENT BEGIN:VEVENT UID:5@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata:20190220T030000 DTEND;TZID=Asia/Kolkata:20190220T170000 DTSTAMP:20221124T122229Z URL:https://aero.iisc.ac.in/events/overview-of-some-industrial-application s-of-university-based-thermo-fluids-research/ SUMMARY:Overview of Some Industrial Applications of University-Based Thermo -Fluids Research DESCRIPTION: Barron and R. Balachandar\n\nUniversity of Windsor\, Canada\n\ nWednesday\, 20th February\, 2019\, 3.00 PM\n\n \n\nThe tools of modern-d ay thermo-fluids research open up a pl ethora of opportunities for interac tions between university researchers and industrial end-users. On the expe rimental side\, measurements include a wide range of devices\, ranging fro m simple flow meters\, pressure gauges\, thermocouples and hotwires to LDA \, LDV\, volumetric and time-resolved PIV. The fundamentals of numerical m odeling of fluid flows and heat transfer are also well-established and the re are many in-house researches\, commercial and open-source codes availab le today. Both approaches\, experimental and computational\, produce an en ormous amount of data which needs to be processed and visualized. Techniqu es for post-processing of large datasets will be discussed\, including POD and various fluid structure identification criteria. While academic resea rchers may strive to develop a better understanding of the flow physics\, industrial researchers want to know how to improve their products. These g oals are not mutually exclusive. Examples to illustrate the use of these t ools and techniques will be drawn from recent work with industrial partner s in the automotive\, food processing\, greenhouse\, mold making and elect ronics industry.\n\n \;\n\nBiography:\n\nDr. Ron Barron\, is Professor Emeritus in the Department of Mathematics and Statistics\, Faculty of Sci ence\, at the University of Windsor\, with cross-appointment to the Depart ment of Mechanical\, Automotive and Materials Engineering. He holds BA and MSc degrees in Mathematics from University of Windsor\, PhD degree in Mat hematics from Carleton University and MSc in Engineering from Stanford Uni versity. He is currentlyDepartment Head\, Associate Dean and Interim Dean of the Faculty of Graduate Studies and Research\, Associate Vice-President Research and Director of Research Services. His research spans across sev eral disciplines\, notably applied mathematics\, mechanical engineering\, civil engineering\, computer science and physics\, focusing on Computation al Fluid Dynamics (CFD) and Numerical Heat Transfer (NHT)\, with special i nterest in software development and industrial applications.\n\nDr. Ram Ba lachandar\, is Professor in the Faculty of Engineering at the University o f Windsor with appointments in the Department of Civil and Environmental E ngineering and in the Department of Mechanical\, Automotive and Materials Engineering. Over the last 25 years\, Dr. Balachandar’s research focus h as been on thermo-fluids engineering and fluid-structure interaction using both experimental and computational tools.\n\n \;\n\nCo-ordinator – Dr. P.S. Kulkarni\, Department of Aerospace Engineering\, IISc\n\nAll are welcome:\n\n \; CATEGORIES:Seminar Series END:VEVENT BEGIN:VEVENT UID:4@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata:20190213T160000 DTEND;TZID=Asia/Kolkata:20190213T170000 DTSTAMP:20221124T122541Z URL:https://aero.iisc.ac.in/events/by-pass-transition-and-re-laminarizatio n-two-sides-of-the-same-coin/ SUMMARY:By-pass transition and re-laminarization - Two sides of the same co in DESCRIPTION:Name of the Speaker:  Prof. Garry Brown\, Dept. of Mechanic al and Aerospace Engineering\, Princeton University\n\nTitle: By-pass tr ansition and re-laminarization - Two sides of the same coin\n\nDate &\; Time: Wednesday\, 13 February 2019\, 4:00 - 5:00 PM\n\nVenue: Auditori um\, Department of Aerospace Engineering\, IISc\, Bangalore\n\nAbstract:\n \nTransition and re-laminarization are good examples of the complexity of many technologically important flows for which predictions from the physic s are needed.  Two routes to ‘transition’ for a laminar boundary laye r are well-known: one\, the classical route via amplifying Tollmien-Schlic hting (T-S) instability waves (and the onset and merging of ‘turbulent s pots’)\, the other\, ‘By-pass’ transition\, (a description coined by Morkovin for the absence of amplifying T-S waves). Boundary layer transit ion has been identified with a rapid increase in wall shear stress (and he at-transfer) but details of the actual mechanisms by which the wall shear stress increases have been elusive.  The talk will describe new insights into ‘roughness induced transition’\, (characteristic of Bypass transi tion).  In particular it will describe from a vorticity point of view a f inal phase which leads to chaotic vorticity (characteristic of turbulence) and a rapid increase in the shear stress at the wall in the absence of an y 2D T-S waves.  The unravelling of what occurs is based on the vorticity transport near the wall (which was elucidated initially by numerical stud ies of turbulent channel flow).  A similar point of view\, but applied to the ‘opposite side of the same coin’\, namely\, ‘re-laminarization ’ has allowed new insights into why re-laminarization occurs in a spatia l turbulent boundary layer subject to a highly favourable pressure gradien t.  It has also been found not to occur in a temporal\, boundary layer (R ayleigh flow) having the same initial  and subject to a rapid acceleratio n of the plate (also a source of spanwise vorticity)\, which is comparable with the acceleration of the free stream flow in the spatial case.  The reason for the different behavior is described and readily appreciated\n\n Speaker:\n\nProf. Garry Brown is the Emeritus Robert Porter Patterson Pro fessor of Engineering at Princeton University. He received a first class H onors Degree in Engineering from the University of Adelaide in 1964\, was awarded a Rhodes scholarship\, completed his D.Phil at Oxford and was then a research fellow/senior research fellow at GALCIT\, Caltech. In 1971 he returned to the University of Adelaide and in 1978 returned to Caltech as full professor. He was asked to serve as Director of the Australian Aerona utical Research Laboratory and held this position from 1981-1990 after whi ch he joined the faculty at Princeton\, serving as Chair of the Department of Mechanical and Aerospace Engineering from 1990 to 1998. His best known work is in the study of turbulence. Fifty years after the inception of th e Journal of Fluid Mechanics\, his 1974 paper with Professor Roshko “On density effects and large structure in turbulent mixing layers\,” was th e most frequently cited paper in the history of the journal. After joining Princeton he explored new research horizons while continuing his abiding interest in turbulence. In 2016 he was the Clark Millikan Visiting Profess or at Caltech and taught a course with Professor Roshko and in 2017 he was the Satish Dhawan Visiting professor at the Indian Institute of Science i n Bangalore where he also taught a course on turbulent shear flows. He has also made significant contributions\, as a consultant in Australia and to the American aerospace industry\, that include the root cause of extreme propeller-induced-vibration of the Lysaght Enterprise\, the root cause of failure and redesign of the solid rocket motor for the Titan IV\, the caus e of early failure and development of the thrust-vectoring system for AIM- 9X and the resolution of critical issues for Tactical Tomahawk and for the Standard Missile-3 Programs. He played a leading role in the failure inve stigation and redesign of early air-cooled test cells for the after-burnin g F100 engine. He is a Fellow of the Institution of Engineers of Australia \, Fellow of the American Physical Society\, and a Fellow of the AIAA\n\nA LL ARE WELCOME\n\nHigh Tea @ 5 PM\n\n------------------------------------ --\n\nP.S. The distinguished lecture series is COMPULSORY for all students (both M.Tech and Ph.D.) of the AE department. END:VEVENT BEGIN:VEVENT UID:3@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata;VALUE=DATE:20180910 DTEND;TZID=Asia/Kolkata;VALUE=DATE:20180913 DTSTAMP:20221124T122229Z URL:https://aero.iisc.ac.in/events/symposium-on-classical-to-computational -aeroelasticity/ SUMMARY:Symposium on Classical to Computational Aeroelasticity DESCRIPTION:Course Coordinator\n\n Prof. Kartik Venkataraman\n\n \;\n\ nCourse Instructors\n\n Prof. Rakesh Kapania (Virginia Tec\, USA)\n\n&nbs p\;\n\nAbstract\n\nTransition from the classical aeroelasticity based on t he linear aerodynamic equations to the computational aeroelastcity based o n the computational fluid dynamics using the non-linear aerodynamic equati ons began in mid 70s. Classical aeroelastcity which is less computer inten sive is still progressing towards use in the preliminary design for more c omplex configurations. Leveraging from the rapid advances in high performa nce computers\, computational aeroelasticity which focuses on accuracy by overcoming the limitations of the linear aerodynamic theory is growing on- par with the classical aeroelasticity. Present symposium addresses progres s to date in both classical and computational aeroelasticity.\n\n \;\n \nEvent Schedule\n\nView/Download Schedule (pdf) CATEGORIES:Conferences END:VEVENT BEGIN:VEVENT UID:2@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata;VALUE=DATE:20171214 DTEND;TZID=Asia/Kolkata;VALUE=DATE:20171216 DTSTAMP:20221124T122229Z URL:https://aero.iisc.ac.in/events/platinum-jubilee-2/ SUMMARY:Platinum Jubilee DESCRIPTION:\n View Flyer\n View Schedule\n Awardees List\n END:VEVENT BEGIN:VEVENT UID:1@aero.iisc.ac.in DTSTART;TZID=Asia/Kolkata:20161219T110000 DTEND;TZID=Asia/Kolkata:20161219T130000 DTSTAMP:20221124T122229Z URL:https://aero.iisc.ac.in/events/you-are-here-home-seminar-uncertainty-q uantification-for-reliability-analysis-and-health-management-in-engineerin g-systems/ SUMMARY:[SEMINAR]: "Uncertainty Quantification for Reliability Analysis and Health Management in Engineering Systems" DESCRIPTION:\n\n\n\nThe Chairman Department of Aerospace Engineering Cordia lly Invite you for a Lecture\n\nTitle:   Uncertainty Quantification for R eliability Analysis and Health Management in Engineering Systems\n\nSpeake r:\nProfessor Sankaran Mahadevan\nJohn R. Murray Sr. Chair in Engineering\ nProfessor of Civil and Environmental Engineering\, Professor of Mechanica l Engineering\nDirector\, NSF-IGERT Doctoral Program in Reliability and Ri sk Engineering and Management\nCo-Director\, Laboratory for Systems Integr ity and Reliability\nVanderbilt University\, Nashville\, TN\, USA\n\n\n\n\ nEvent Date:\n\nMonday\, December 19\, 2016 - 11:00\n\n\n END:VEVENT BEGIN:VTIMEZONE TZID:Asia/Kolkata X-LIC-LOCATION:Asia/Kolkata BEGIN:STANDARD DTSTART:20151220T110000 TZOFFSETFROM:+0530 TZOFFSETTO:+0530 TZNAME:IST END:STANDARD END:VTIMEZONE END:VCALENDAR