Qualification: 
Ph.D, M.Tech
Email: 
sr_nagaraja@blr.amrita.edu

Dr. Nagaraja S. R. currently serves as Chairperson at the Department of Mechanical Engineering, School of Engineering, Amrita Vishwa Vidyapeetham, Bengaluru campus.

Education

  • Ph.D. in Engineering
    From: Birla Institute of Technology, Mesra, Ranchi
  • M.Tech. in Production Engineering Systems Technology
    From: Mysore University
  • B.Tech./B.E. Mechanical Engineering
    From: N.I.T. Surathkal

Professional Appointments

Year Affiliation
2008 – till date Amrita Vishwa Vidyapeetham, Bengaluru Campus
1991 - 2008 Sir M. Visvesvaraya Institute of Technology, Bengaluru
1986 - 1989 Siddaganga Institute Of Technology, Tumakuru

Major Research Interests

  • Shock Waves and their applications, Hypersonic Flows, Fluid Structure Interactions

Membership in Professional Bodies

  • SAE India
  • Indian Society for Technical Education (ISTE)
  • Society for Shock Wave Research – India
  • American Society for Mechanical Engineers (ASME)

Publications

Publication Type: Conference Paper

Year of Publication Title

2021

Sachin Pullil, Vaibhav, N., Sanjay, R., and Nagaraja S. R., “Parametric Study of Blast Wave Formation in a Shock Tube”, in Proceedings of International Conference on Thermofluids, Singapore, 2021.[Abstract]


Blast waves are formed when there is a sudden release of energy from a point in space, like, from an explosion. These waves propagate through air, come into contact with structures or human beings, and proceed to cause fatal or irreversible damage. Many methods have been developed to attenuate blast waves. However, to conduct physical experiments, the use of real explosives is for the risk of collateral damage. Thus, shock tubes are utilized to create blast waves within a confined region so that they can be studied safely. When the diaphragm bursts, a shock wave is formed in the driven section of the tube and, eventually, the pressure profile of the wave changes to that of a blast wave. The paper focuses on a parametric study of the variation of driver section length and pressure in the formation of blast waves in a shock tube. The distance at which the blast wave forms increases with increasing driver section pressure and length. The experimental results show that the pressure wave closely matches with that of Friedlander waveform at higher driver pressures.

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2021

V. G. Srujan, Subramanian, D., Nagaraja S. R., Rathinam, B., and Ravet, F., “Validation of Eulerian-Lagrangian Spray Atomization Modeling against Gasoline Fuel”, in SAE Technical Paper, 2021.[Abstract]


Combustion in any engine starts with the injection of fuel into the combustion chamber. Atomization of fuel and its mixing plays a vital role in determining the suitable air-fuel (A/F) ratio. Appropriate A/F ratio determines the amount of energy release and pollutant formation for standard engines. Thus an accurate prediction of these processes is required to perform reliable combustion and pollutant formation simulations. In this study, the Eulerian-Lagrangian Spray Atomization (ELSA) model is implemented as a Computational Fluid Dynamics (CFD) tool for the prediction of spray behavior. Past studies performed on diesel fuel suggest good agreement between experiment and simulation indicating the model’s capability. The study aims to validate the ELSA model for gasoline fuel against the test results obtained from Renault and against the pure Lagrangian spray model. The simulations have been performed using CONVERGE CFD v2.4.18. A constant-volume spray bomb model consisting of a SAC is simulated across different operating conditions with variations in temperatures and pressures. The nozzle geometry has been simplified and is assumed to be circular in cross-section. Macroscopic and microscopic spray characteristics, namely, Spray (Liquid) Penetration Length and Sauter Mean Diameter (SMD), are compared. The first section of the results deals with a comparison between simulation and test data, whereas the second and third sections describe the comparison of spray characteristics between the ELSA and Lagrangian spray description against the test results and the variation of spray characteristics concerning state properties, respectively. The results obtained using the ELSA model are in good agreement with the experimental results, but require further enhancement when compared against the Lagrangian description. The spray prediction furthermore is in accordance with the spray behavior and is theoretically explainable.

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2019

Rajesh M and Nagaraja S. R., “An autonomous system of mobile robots for search in disaster affected sites”, in 2019 3rd International conference on Electronics, Communication and Aerospace Technology (ICECA), 2019.[Abstract]


Search and rescue operations during disasters are normally unsafe and tedious to human firefighters. As an alternative, an autonomous system of mobile robots, which can do the search and rescue operation, will be an efficient mechanism. Most of the systems consisting of mobile robots involve human interaction and control largely, which is again less efficient. So development of an autonomous system of mobile robots which can explore an area and complete the search and rescue operation is important. Such a system should have the options to explore an area in an efficient way by the coordination of robots each other and localization schemes. An autonomous mobile robots system is implemented which explores an unknown area and builds a map of the area. The robots coordinate with each other by building local maps and sharing them with others to build the global map. The robots localize themself using trilateration localization scheme. Marking the area covered by each robot is done by placing RF ID tags in an optimized way. The proposed scheme is implemented in hardware using the FireBird V mobile robots.

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2018

P. Visakh, Akhil, J., and Nagaraja S. R., “Effect of Counter Flowing Jet on Heat Transfer and Drag in Hypersonic Re-entry Vehicle”, in IOP Conference Series: Materials Science and Engineering, 2018, vol. 377.[Abstract]


<p>All the re-entry vehicles usually travel at hypersonic velocities, there are some design constraints pertaining to them such as aerodynamic drag and heat, which are mutually conflicting. A sharp edged slender body offers longer range and lesser drag but it causes higher aerodynamic heat. Generally, blunt shaped nose is used for the re-entry vehicles as it can disperse the accumulated heat to the surroundings better than sharp edged bodies. The current work focuses on reduction of aerodynamic heating by the introduction of a single jet injection on the stagnation point. Different jet angle configurations are used for the analysis by maintaining the angle of attack of the body constant. It is found that for body at 6-degree angle of attack the optimum jet angle is 9 degrees and the corresponding reduction in peak heat flux is 22.7% compared to the heat flux when the jet is at zero degrees and 33% compared to the case without jet. © Published under licence by IOP Publishing Ltd.</p>

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2018

B. R. Pankaj, Rangarajan, S., and Nagaraja S. R., “Analytical Performance Analysis of Cross Flow Louvered Fin Automobile Radiator”, in MATEC Web of Conferences, 2018, vol. 172.[Abstract]


The objective of the present paper is to propose an analytical model for calculating performance parameter of a radiator having rectangular tube with louvered fins. The theoretical effectiveness, heat transfer rate, outlet temperatures of both air and coolant are determined using effectiveness-NTU method. The coolant and air side pressure drop is also calculated. The proposed procedure is validated with experimetal results available in the literature and the GT model. It is found that the maximum deviation in the heat transfer rate calculated from proposed model is 10.97%, the coolant and air outlet temperatures is 2.75% and variation in pressure drop is about 3.29%. © 2018 The Authors, published by EDP Sciences.

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2018

, Akhil, M., Ram, S., Gopaiah, V., Koundinya, S., and Nagaraja S. R., “Study of the effects of Shockwaves on Nano fluids”, in IOP Conference Series: Materials Science and Engineering, 2018, vol. 310.[Abstract]


Nanofluids are fluids with nanoparticles dispersed in them. Due to the presence of Nano particles, these fluids exhibit unique properties that can used in various applications such as heat exchangers and in medical fields. However, due to agglomeration, the size of these particle increases, reducing their efficiency. In order to break the agglomeration, we are passing shockwaves in the fluid. Shockwaves theoretically carry energy which can be used to break the agglomerating particles. In this paper, silver nanoparticles were synthesized using silver nitrate. Tri sodium citrate was used as the reducing agent. Shock waves were passed to the fluid containing silver Nano particles. The changes in the Nano fluid was measured by a UV-Vis Spectrophotometer. With each shock passed, the fluid's absorbance and wavelength peak was measured and compared with Nano fluid without shock.

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2017

G. K. Nambiar, Sriram, M., Dharanidhar, M., Nair, P. G., and Nagaraja S. R., “Design and Fabrication of hand operated mini Shock Tube”, in IOP Conference Series: Materials Science and Engineering, 2017, vol. 225.[Abstract]


Shock waves have been used for medical, biological and industrial applications. In this paper design, frication and calibration of a low cost mini shock tube is presented. Commercial FEM software COMSOL multiphysics is used for analysis of shock tube flows. The hand operated mini shock tube is capable of generating shock Mach numbers up to 1.8, peak over pressures up to 8 bar. Experimental and theoretical values of pressure ratio jump primary and reflected shock closely agree with each other. The fabricated shock tube is used for free forming of metallic foils.

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2017

S. A. Harsha, Rizwan, M., Kuldeep, S., A. Prasad, G., Akhil, J., and Nagaraja S. R., “Parametric Study of Cantilever Plates Exposed to Supersonic and Hypersonic Flows”, in IOP Conference Series: Materials Science and Engineering, 2017, vol. 225.[Abstract]


Analysis of hypersonic flows associated with re-entry vehicles has gained a lot of significance due to the advancements in Aerospace Engineering. An area that is studied extensively by researchers is the simultaneous reduction aerodynamic drag and aero heating in re-entry vehicles. Out of the many strategies being studied, the use of aerospikes at the stagnation point of the vehicle is found to give favourable results. The structural stability of the aerospike becomes important as it is exposed to very high pressures and temperatures. Keeping this in view, the deflection and vibration of an inclined cantilever plate in hypersonic flow is carried out using ANSYS. Steady state pressure distribution obtained from Fluent is applied as load to the transient structural module for analysis. After due validation of the methods, the effects of parameters like flow Mach number, plate inclination and plate thickness on the deflection and vibration are studied.

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2017

C. H. V. L. C. S. Pavan Kumar, C. Reddy, H., L. Sai, R., Kumar, K. S. S. Dharani, and Nagaraja S. R., “Attenuation of Shock Waves using Perforated Plates”, in IOP Conference Series: Materials Science and Engineering, 2017, vol. 225.[Abstract]


The shock/blast waves generated due to explosions cause wide spread damage to the objects in its path. Different techniques have been used to attenuate shock wave over pressure, to reduce the catastrophic effects. Perforated plates can be used effectively to attenuate the shock wave pressure. In this paper shock wave interaction with perforated plates is simulated using COMSOL multiphysics software. The pressure drop varied from 43.75% to 26% for porosity varying from 10% to 40.

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2017

G. Rohit, Manaswini, D., Kotebavi, V., and Nagaraja S. R., “Performance study of thermo-electric Generator”, in AIP Conference Proceedings, 2017, vol. 1859.[Abstract]


Devices like automobiles, stoves, ovens, boilers, kilns and heaters dissipate large amount of waste heat. Since most of this waste heat goes unused, the efficiency of these devices is drastically reduced. A lot of research is being conducted on the recovery of the waste heat, among which Thermoelectric Generators (TEG) is one of the popular method. TEG is a semiconductor device that produces electric potential difference when a thermal gradient develops on it. This paper deals with the study of performance of a TEG module for different hot surface temperatures. Performance characteristics used here are voltage, current and power developed by the TEG. One side of the TEG was kept on a hot plate where uniform heat flux was supplied to that. And the other side was cooled by supplying cold water. The results show that the output power increases significantly with increase in the temperature of the hot surface.

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2016

P. Chinmaye and Nagaraja S. R., “Obstacle avoidance in a solar powered autonomous vehicle”, in 2016 IEEE International Conference on Computational Intelligence and Computing Research (ICCIC), 2016.

2016

G. V. P. Reddy and Nagaraja S. R., “Image based obstacle detection and path planning for solar powered autonomous vehicle”, in 2016 International Conference on Robotics and Automation for Humanitarian Applications (RAHA), 2016.

2014

C. Nimisha, Dr. Sreeja Kochuvila, Sudarshan, T. S. B., and Nagaraja S. R., “Flexible foot system for a biped robot”, in International Conference on Circuits, Communication, Control and Computing, 2014.

2014

R. Reddy and Nagaraja S. R., “Integration of robotic arm with vision system”, in 2014 IEEE International Conference on Computational Intelligence and Computing Research, 2014.

Publication Type: Journal Article

Year of Publication Title

2019

B. V. N. Pramod, Raj, J. Prudhvi, Parashar, C. H., Kartha, A., and Nagaraja S. R., “Attenuation of shock waves by using porous media”, AIP Conference Proceedings, vol. 2080, p. 030015, 2019.

2019

V. M. Prashanth and Nagaraja S. R., “Effect of microjet on heat and drag in hypersonic flows”, AIP Conference Proceedings, vol. 2200, p. 020066, 2019.[Abstract]


Aerodynamic drag and heat are some of the most promising design constraints which play a vital role in aircrafts that travel with Mach number greater than 5. Higher aerodynamic heat is caused by sharp edged bodies. Therefore, blunt shape nose is preferred if the nose material puts an upper limit on aerodynamic heating. Larger nose radius allows the heat to spread over a large area and produce lower peak loads. The current work focuses on addition of high-speed fluid which is generally called as jet on a blunt body by varying the angle of attacks of both the jet and the body using Ansys Fluent software. Aerodynamic heating causes damage to the nose of hypersonic aircrafts. High bluntness leads to drag production at hypersonic speeds. The body is kept at different angle of attacks with jet and without jet and wall heat transfer is observed at the stasis point. The commencement of jet for 0° also deflates greatest heat transfer value at the stasis point by 17% although correlated along with body at 0° in the absence of jet. Coefficient of drag values i.e. Cd values doesn’t change much and these values flutter among 0.0043 and 0.00438 for a fixed ratio of pressures. From this work it can be concluded that initiation of micro jet is the prime approach to avert vast heat.
REFERENCES

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2019

V. Vattaparam Parthan, Shyamkumar, P. I., and Nagaraja S. R., “Canopy design to minimize restrictions and maximize heat transfer”, AIP Conference Proceedings, vol. 2200, p. 020079, 2019.[Abstract]


A Canopy or an Enclosure is a crucial part of a genset which protects the generator from external environmental factors and maximizes its efficiency. Most of the genset enclosures are designed to meet the noise requirements set by legal authorities but it is also important that such designs can expel the heat generated by different parts of the generator such as engine, alternator, and radiator. This report focusses on the design of a Canopy for QSK 60 G4 Cummins Genset to minimize the restrictions and simultaneously maximize the heat transfer across the system. This method of optimizing the two objectives i.e. pressure drop and heat transfer are carried out by parametrizing the louver angles and length of louvers for two different models on ANSYS. Genetic Aggregation in RSO (Response Surface optimization) is used to constrain the objective functions to the limiting range which is set as per the experimental tests carried out for detecting the pressure drop and LAT (Latent Ambient Temperature).
REFERENCES

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2018

S. Vishal, Nair, V. V., Teja, P. Sai, Rajan, S., Akhil, J., and Nagaraja S. R., “Parametric Study of Hypersonic Flow over Different Bi-Cone Configurations”, IOP Conference Series: Materials Science and Engineering, vol. 377, p. 012171, 2018.[Abstract]


A series of numerical simulations are conducted on bi-cone shaped axisymmetric geometries using ANSYS FLUENT commercial code. Eight bi-cone geometries were simulated with first cone half-angle fixed at 25° and varying the second cone half-angle varying from 10° to 45° with an increment of 5°. The simulations were conducted in hypersonic flow regime at three different Mach numbers of 6, 8, 10 with geometries approximated as 2-D axisymmetric. Shock interactions observed essentially fall in the TYPE VI and TYPE V category. The simulations accurately predicted these shock interactions, the size of flow separation regions, the surface pressure, and density variations across the geometries considered. It is observed that when the second cone angle is greater than the first cone angle larger values of pressure and heat flux were encountered at flare angle whereas when the second angle is less than the first cone angle, smaller values of pressure and heat flux were encountered at the second cone.

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2018

S. Shali, Parol, J., and Nagaraja S. R., “Identification of second spectrum of a Timoshenko beam using differential transform method”, Journal of Engineering Science and Technology, vol. 13, pp. 893-908, 2018.[Abstract]


In the present work, the vibration characteristics of a Timoshenko beam are examined using Differential Transform Method (DTM) with the end conditions hinge-hinge, fix-hinge, fix-fix and fix-free. The frequencies are computed for the beam with the length to depth ratio (L/H) of 2, 3, 5, 10 and 20. The results obtained from the DTM are compared with exact values and finite element results. DTM analysis shows that the second spectrum of frequency is observed in beams which are comparatively thick (L/H ≤ 10), with hinge-hinge end condition. Eigenfunctions for both frequency spectra are derived using this method. The convergence analysis of frequencies of a Timoshenko beam obtained using DTM is also presented. The second set of frequencies are not reflected in the vibration of beams with end conditions other than hinge-hinge. The mode shapes are presented for the pure shear mode and the first three bending and shear modes of hinge-hinge supported Timoshenko beam.

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2017

K. G.G., Akhil,, and Nagaraja S. R., “Drag reduction for hypersonic re-entry vehicles”, International Journal of Mechanical Engineering and Technology, pp. 878-885, 2017.

2016

S. Shali, Nagaraja S. R., and Jafarali, P., “Non-uniform beam vibration using Differential Transform Method”, IOP Conference Series: Materials Science and Engineering, vol. 149, p. 012158, 2016.[Abstract]


The paper focuses on the vibration characteristics of non-uniform Euler- Bernoulli beam using Differential Transform Method (DTM). DTM is a numerical method to solve differential equations where the governing equations are reduced into a set of polynomials. Non-uniformity is considered corresponding to linear variation in breadth and height of the beam. The effect of taper ratio on the fundamental frequency of tapered beams is also analysed. The method has proved to be accurate, simple and effective for eigenvalue analysis. For the two cases of non-uniform beam analysed, the frequency computed by the method of differential transform is found to be comparable with the previously available results.

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2016

A. R., N.R, N., P, S., P, K., and Nagaraja S. R., “CFD analysis of Co flow jet airfoil”, Indian Journal of Science and Technology, 2016.

2016

N. Sreekanth, Nagaraja S. R., and Akhil, J., “Design and Analysis of Secondary Spike on Blunt Head”, Indian Journal of Science and Technology, vol. 9, 2016.[Abstract]


The present paper investigates the heat flux and drag reduction techniques on a hypersonic re-entry vehicle. Many
researchers have reported a reduction in these parameters by the introduction of an aero spike at the stagnation point of
the blunt head of a re-entry vehicle. The effect of introducing a secondary surface (called the secondary spike), along with
the aero spike, on the blunt head is discussed in this work. The study has been carried out by varying the location of the
secondary spike with respect to the axis of the vehicle for a set of free stream conditions. Also, the effect of variation in free
stream conditions on a re-entry vehicle with a primary and secondary spike has been investigated. It has been observed
that some configurations work well for some free stream conditions but fail in comparison to a single spiked body for some
other conditions.

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2016

A. M. Nair and Nagaraja S. R., “Simulation and analysis of protrusions on flat plate at hypersonic speeds”, Indian Journal of Science and Technology, 2016.[Abstract]


This paper presents investigation into the complex phenomena that occur in the vicinity of three dimensional forward
facing steps mounted on a flat plate in hypersonic flow of Mach number 8. The dependence of the flow field on geometry
parameters like height of protrusion and deflection angle is also studied. Vortices generated at the separation location
seemed to wrap around the protuberance, causing high surface heating in the separated region, with the hotspot at the foot
of the shock. For lower deflection angle model, the protuberance did not have much effect upstream, but turbulence was
observed to the side of the protuberance. The flow remained more or less attached, suggesting nominal heating in the front
of the protrusion. As the deflection angle increased, separation phenomena was more visible and hence the recirculation
zone. For un-separated flow cases, the protrusion height had less effect on the surface heating. But when the flow was
separated, the extent of flow separation region was large, indicating higher surface heating.

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2015

P. S.B and Nagaraja S. R., “Comparative study of micro and macro shock tube flows using CFD”, International Journal of Applied Engineering Research, 2015.

2015

K. K and Nagaraja S. R., “Solar powered terrestrial ground exploration vehicle”, International Journal of Applied Engineering Research, vol. 10, no. 69, 2015.

2015

P. Pa Tekale and Nagaraja S. R., “Designing and development of an autonomous solar-powered robotic vehicle”, Advances in Intelligent Systems and Computing, vol. 332, pp. 163-168, 2015.[Abstract]


In this paper, design and fabrication of a solar-powered robotic vehicle is presented. The energy for the vehicle is supplied by two solar panels of 5 W each. For efficient energy management, a charging system is designed. The charging is independent of the vehicle movement. Two batteries are used so that one is charging, while other is discharging. A charge controller is also designed so as to provide direct power supply to the connected load in case both batteries fail. © Springer India 2015.

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2012

Nagaraja S. R., G., D. Rakesh S., Prasad, J. Kb, Barhai, P. Kb, and Jagadeesh, Gc, “Investigations on micro-blast wave assisted metal foil forming for biomedical applications”, International Journal of Mechanical Sciences, vol. 61, pp. 1-7, 2012.[Abstract]


The deformation dynamics of metal foils (&lt;0.25 mm thick) subjected to micro-blast wave are presented in this paper. The energy of micro-blast wave emanating from the open end of a polymer tube is used to deliver micro-particles for bio-medical applications. In these experiments metal foils are used to transfer the energy of the micro-blast wave to the micro-particles. Using cubic root scaling law the over pressure of the blast wave at the open end of the polymer tube is estimated and using this peak plate over pressure is estimated. The finite element analysis is used to estimate the velocity profile of the deforming metal foils. The finite element analysis results are compared with experimental results for the maximum deformation and deformed shape. Based on the deformation velocity, metal foil to be used for experiments is selected. Among the materials investigated 0.1 mm thick brass foil has the maximum velocity of 205 m/s and is used in the experiments. It is found from finite element analysis that the particles deposited within a radius of 0.5 mm will leave the foil with nearly equal velocity (error &lt;5%). The spray cone angle which is the angle of deviation of the path of particles from the axis of the polymer tube is also estimated and found to be less than 7° up to a radius of 0.75 mm. Illustrative experiments are carried out to deliver micro particles (0.7 μm diameter tungsten) into plant tissues. Particle penetration depth up to 460 μm was achieved in ground tissue of potato tuber. © 2012 Elsevier Ltd. All rights reserved.</p>

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2012

Nagaraja S. R., Prasad, J. Kb, and Jagadeesh, Gc, “Theoretical-experimental study of shock wave-assisted metal forming process using a diaphragmless shock tube”, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 226, pp. 1534-1543, 2012.[Abstract]


The use of high-velocity sheet-forming techniques where the strain rates are in excess of 102/s can help us solve many problems that are difficult to overcome with traditional metal-forming techniques. In this investigation, thin metallic plates/foils were subjected to shock wave loading in the newly developed diaphragmless shock tube. The conventional shock tube used in the aerodynamic applications uses a metal diaphragm for generating shock waves. This method of operation has its own disadvantages including the problems associated with repeatable and reliable generation of shock waves. Moreover, in industrial scenario, changing metal diaphragms after every shot is not desirable. Hence, a diaphragmless shock tube is calibrated and used in this study. Shock Mach numbers up to 3 can be generated with a high degree of repeatability (±4 per cent) for the pressure jumps across the primary shock wave. The shock Mach number scatter is within ±1.5 per cent. Copper, brass, and aluminium plates of diameter 60 mm and thickness varying from 0.1 to 1 mm are used. The plate peak over-pressures ranging from 1 to 10 bar are used. The midpoint deflection, circumferential, radial, and thickness strains are measured and using these, the Von Mises strain is also calculated. The experimental results are compared with the numerical values obtained using finite element analysis. The experimental results match well with the numerical values. The plastic hinge effect was also observed in the finite element simulations. Analysis of the failed specimens shows that aluminium plates had mode I failure, whereas copper plates had mode II failure. © 2011 IMechE.

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Publication Type: Conference Proceedings

Year of Publication Title

2019

A. A.K., G, N., and Nagaraja S. R., “Design and development of a BWB aircraft”, AIP Conference Proceedings. 2019.

2019

S. S.N and Nagaraja S. R., “Analysis on a blunt cone with protrusion in hypersonic flow”, AIP Conference Proceedings. 2019.

2019

N. Akshay and Nagaraja S. R., “Transient Analysis of a Blunt Body with Cylindrical Protrusion in Hypersonic Flow”, IConAMMA – 2018, vol. 577. IOP Publishing, ASE, Bangalore, p. 012178, 2019.[Abstract]


Numerical analysis of a blunt body with protrusion in hypersonic flow having Mach number 8 is analysed using ANSYS-FLUENT. Transient analysis gives a better understanding of the flow field, separation of the flow from body, time taken for achieving steady state. 3D analysis has done. The variations of the pressure with respect to time at different locations on the body are obtained. The peak pressure at the separation point is 38% more than the steady state pressure. Pressure fluctuates inside the separation region.

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2017

S. Shali, Nagaraja S. R., and Jafarali, P., “Vibration of non-uniform rod using Differential Transform Method”, IOP Conference Series: Materials Science and Engineering, vol. 225. Institute of Physics Publishing, 2017.[Abstract]


The present paper analyses the vibration characteristics of non-uniform rods using Differential Transform Method. The method is very effective in solving ordinary and partial differential equations. The governing equations are transformed into a set of polynomials and the solution of these algebraic equations gives the desired frequency. Method is implemented for fix-free and fix-fix end conditions of a non-uniform rod. It is seen that the lower modes are sensitive to taper ratio in case of fix-free rod and fix-fix case frequency is same as that of uniform rod for different taper ratios. The method has proved to be accurate, simple and effective for eigenvalue analysis

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2017

J. S. Chaitanya, Prasad, A., Pradeep, B., Harsha, P. L. N. Sri, S. Shali, and Nagaraja S. R., “Vibrational Characteristics of AGARD 445.6 Wing in Transonic Flow”, IOP Conference Series: Materials Science and Engineering, vol. 225. Institute of Physics Publishing, 2017.[Abstract]


This paper presents the application of Computational Fluid Dynamics (CFD) and Fluid Structure Interaction in ANSYS to do vibrational analysis on an aircraft wing in transonic region. A simulation study is conducted on a wing by modelling it in a solid modelling software. Further CFD analysis is performed at different Mach numbers to identify pressure variations at different locations on the wing. Transient structural analysis is carried out to study the variations in displacement of the wing with time. The post processing is done for determining the structural frequency and thereby to establish the flutter boundary in the transonic range.

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2017

Basavaraj Noolvi, Raja, S., and Nagaraja S. R., “Actively Tuned Vibration Absorber using Smart Adaptive Composites”, Materials Today: Proceedings, vol. 4. Elsevier Ltd, pp. 3506-3512, 2017.[Abstract]


Shape memory materials (SMMs) are known for their excellent vibration absorption properties. The current work is focused on study of vibration absorption characteristics of Smart Adaptive Composites (Shape Memory Composites) (SACs), as tuned vibration absorbers. Thin cantilever plate of SAC works as the absorber system in the configuration.

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2009

Nagaraja S. R., Prasad, J. K., .K.Barhai, P., Jagadeesh, G., and G., D. Rakesh S., “Studies on forming of thin metal foils for bio-medical applications of shock waves”, ISSW27 (International Symposium on Shockwaves) held in Russia. - 2009. 2009.

2005

Nagaraja S. R., Jagadeesh, G., and Prasad, J. K., “Theoretical Studies on Shock wave assisted Metal forming process”, 25th International Symposium of Shock Waves, ISSW 2005. 2005.

Keynote Addresses/Invited Talks/Panel Memberships

  • 2nd National Symposium on Shock Waves NSSW2 - 2012

Courses Taught

  • Gas Dynamics and Jet Propulsion, Gas Turbines and Jet Propulsion, Turbomachinery, Aerodynamics, Computational Methods in Fluid Flow and Heat Transfer, Advanced Heat Transfer, Numerical Methods

Student Guidance

Undergraduate Students

Sl. No. Name of the Student(s) Topic Status Year of Completion
1 Sachin Pullil (BL.EN.U4MEE14080) Vaibhav N. (BL.EN.U4MEE14054) Sanjay R. (BL.EN.U4MEE14508) Parametric Study of Blast Wave Formation in Shock Tube Completed 2018
2 Anand A Koushik (BL.EN.U4MEE14009) Ganesh Nair (BL.EN.U4MEE14031) Design and Development of an unmanned aerial Vehicle Completed 2018
3 B V N Pramod (BL.EN.U4MEE14022) Jami Prudhvi Raj (BL.EN.U4MEE14504) Chilukuri Parashar (BL.EN.U4MEE14027) Aditya Kartha (BL.EN.U4MEE14003) Attenuation of Shock Waves by using porous Medium Completed 2018
4 CH V L C S Pavan Kumar(BL.EN.U4MEE13503) C. Hitesh Reddy (BL.EN.U4MEE13025) L Rahul Sai (BL.EN.U4MEE13060) K. S. S. Dharani Kumar (BL.EN.U4MEE13054) Attenuation of Shock Waves using Perforated Plates Completed 2017
5 M. Dharanidhar (BL.EN.U4MEE12028) M. Sriram(BL.EN.U4MEE12029) Pashant G. Nair (BL.EN.U4MEE12038) Gautham K. Nambiar (BL.EN.U4MEE12509) Design and Fabrication of Mini Shock tube Completed 2016
6 Nandu Rajeevan nair (BL.EN.U4MEE12505) R. Abinav (BL.EN.U4MEE12507) Sravan P. (BL.EN.U4MEE12050) Pradeesh Kumar (BL.EN.U4MEE12037) CFD Analysis of Co-Flow JET Airfoil Completed 2016
7 Arjun R (BL.EN.U4MEE12002) P Shiva Sai (BL.EN.U4MEE12506) B Sruthi Reddy (BL.EN.U4MEE12508) Design and Evaluation of a Waverider Completed 2016
8 K Kalasagarreddi (BL.EN.U4MEE11032) Sobhan Prem Sai K(BL.EN.U4MEE11057) G Vinay Kumar (BL.EN.U4MEE11021) Simulation of Shock wave assisted free and shape forming of metallic plates in a shock tube Completed 2015
9 Nikhil Chandrasekhar(BL.EN.U4MEE10043) Jagannath Kamath(BL.EN.U4MEE10026) Rijeek K V (BL.EN.U4MEE10051) Concentrated PV-Thermal Sytems Completed 2014
10 Aditya Kumar (BL.EN.U4MEE10001) Arun Sathish S K(BL.EN.U4MEE10008) Gangadharan R (BL.EN.U4MEE09019) Analysis of Conjugate Heat Transfer in a Solid Rocket Motor Nozzle Completed 2014
11 V. Naveen Kumar reddy (BL.EN.U4MEE10063) N. Vinayaka Moorthy (BL.EN.U4MEE10066) B. Yashwanth (BL.EN.U4MEE10501) Waste Heat Recovery by Thermo- Electric Genertion Completed 2014
12 Bhartendu Tavri(BL.EN.U4MEE10502) CFD Analysis of a Blade Cascade for a Radial Turbine in a Hydraulic Tunnel Completed 2014
13 Mahesh N (BL.EN.U4MEE09032) Shreyas Kamath (BL.EN.U4MEE09046 Suraj Natarajan (BL.EN.U4MEE09051) CFD Analysis of Shock Structure Interaction Completed 2013
14 Aneesh Ravikumar(BL.EN.U4MEE09008) Irfan Malik (BL.EN.U4MEE09033) R Madan (BL.EN.U4MEE09042) Siva Sembian (BL.EN.U4MEE09048) Flow Visualisation Over Different Bodies Inside a Wind Tunnel Completed 2013
15 Asher Reginald Antao(BL.EN.U4MEE08011) Bharat R. Beltur (BL.EN.U4MEE08015) C Akhila(BL.EN.U4MEE08017) Sashank Ravi(BL.EN.U4MEE08071) Design Fabrication and Testing of a Sub-Sonic Wind Tunnel Completed 2012
16 Adarsh Kumar(BL.EN.U4MEE08003) Alavala Harin Reddy(BL.EN.U4MEE08007) Gampa Sharan(BL.EN.U4MEE08027) Lingutla Lakshmi Narayana (BL.EN.U4MEE08033) CFD Modeling of Shock Waves and Micro Jets Completed 2012
17 Siddharth Porwal (BG107ME053) Production Characterization and Hot Workability of CuZr Based Ternary Shape Memory Alloys Completed 2011
18 Manpreet Singh(BG107ME024) Sanskar Shrivastava (BG107ME047) Sharanya K Prasad(BG107ME051) Impact of Low Calorific Value Fuels and Syngas on gas turbine performance Completed 2011

Postgraduate Students

Sl. No. Name of the Student(s) Topic Status Year of Completion
1. Choraghe Shweta Laxman (BL.EN.P2TSE18002) ANALYSIS OF SHOCK TRAINS IN AN ISOLATOR Completed 2020
2. N Hareesh Bharadwaj (BL.EN.P2TSE18005) Drag Reduction And Heat Transfer Study On Blunt Bodies Using Jets Completed 2020
3. Veena V. Parthan(BL.EN.P2TSE17015) Canopy Design to minimize Restrictions and Maximize Heat Transfer Completed 2019
4 Shaik Nawaz Sharief (BL.EN.P2TSE17012) Analysis on Blunt Cone with Protrusion in Hypersonic Flow Completed 2019
5 V. G. Srujan (BL.EN.P2TSE17014) Validation of Eulerian Lagrangian Spray Atomization(Elsa) Modeling on Gasoline applications Completed 2019
6 Pankaj Ravindra Badgujar (BL.EN.P2TSE16003) Analytical Study on Radiator Performance using Matlab Completed 2018
7 Akshay N. (BL.EN.P2TSE16002) Analysis of a Blunt body with Protrusion in Hypersonic Flow Completed 2018
8 Visakh P (BL.EN.P2TSE15006) Effect of counter Flowing Jet on Heat Transfer and Draging Hypersonic Re-Entry Vehicle Completed 2017
9 Mithun Chandrakumar (BL.EN.P2TSE15003) Study of the Effect of Protrusions in Hypersonic Flows Completed 2017
10 Chinmaye P. (BL.EN.P2TSE14002) Obstacle Avoidance for a Solar Powered Autonomous Vehicle Completed 2016
11 Aathira M Nair. (BL.EN.P2TSE14001) Unsteady Flowfield over two-dimensional & Three-dimensional rectangular cavities Completed 2016
12 Susheel Kumar Babu Patil. (BL.EN.P2TSE13009) Simulation of Shock Tube Vibrations in a diaphragm opening process and designing a contour Nozzle Completed 2015
13 Samprathy Manish (BL.EN.P2TSE13006) Attenuation of Shock Waves Completed 2015
14 Pankaj P. Tekale (BL.EN.P2EBS12026) Designing and Development of an Autonomous Solar Powered Robotics Vehicle Completed 2014
15 Madem Ravitej Reddy (BL.EN.P2EBS12014) Integration of Robotics of with Vision System Completed 2014
16 Mithun P. (BL.EN.P2EBS11014) Co-Ordiante Based Autonomous Robotic ARM with Intelligence Completed 2013
17 Saneesh Kumar G. (BL.EN.P2EBS11020) Efficient Obstacle Avoidance for Mobile Robots Completed 2013
18 D N Kiran Pandiri (BL.EN.P2EBS10004) Mobile Robot Navigation with Obstacle Avoidance in an Unknown Environment Completed 2012

Research Scholars

Sl. No. Name of the Student(s) Topic Status Year of Completion
1. Ms. Shali S. Aerodynamic Flutter Analysis Ongoing  
2. Mr. A.A. Nippun Kumaar Navigation Techniques for Autonomous Mobile Service Robot Ongoing  
3. Mr. Rajesh M. Effective Localization & Communication Protocol for Mobile Robots Ongoing