M.Tech, B-Tech

Shali S is currently serving as Deputy Controller of Examinations and Assistant Professor (Sr. Gr.) in the Department of Mechanical Engineering, Amrita School of Engineering, Bengaluru. She is pursuing her Ph.D. in the area of vibration charecteristics in Hypersonic flow. Her areas of research include Structural vibration, Elasticity, Hypersonic flow, Aeroelasticity.


  • Ph.D. in Mechanical Engg. (Pursuing)
    From: Amrita Vishwa Vidyapeetham
  • M.Tech. in Offshore Structures(2002-2004)
    From: NIT, Calicut
  • B.Tech. Civil Engg. (1997-2001)
  • From: NSS College of Engg. Palakkad

Professional Appointments




Lecturer in the Department of Applied Mechanics, Amrita School of Engg., Ettimadai


Lecturer in the Department of Civil Engg., Amrita School of Engg., Bengaluru

2008- 2019

Assistant Professor(Sr.Gr) Department of Mechanical Engg., Amrita School of Engg., Bengaluru

2019- till date

Assistant Professor (Sr.Gr) , Department of Mechanical Engg.,ASE,Bengaluru & Deputy Controller of Examinations,Amrita School of Engg. Bengaluru

Research & Management Experience

  • Actively involved in co-ordinating student activities of the campus. Served as the Vice Chair for the Student activity ensemble Amritadhara continuously for five years from 2014 to 2019.

Major Research Interests

  • Aeroelasticity
  • Numerical Methods in Structural Engineering
  • Vibrational analysis of Structural elements in subsonic and supersonic flow

Membership in Professional Bodies

  • Life member of the Indian Society of Theoretical and Applied Mechanics from 2014.


Publication Type: Conference Paper

Year of Publication Title


S. Pai, Chandy, P. Poly, Krishnan, R. A., and S. Shali, “2D analysis of waverider in hypersonic flow”, in 1ST INTERNATIONAL CONFERENCE ON MANUFACTURING, MATERIAL SCIENCE AND ENGINEERING (ICMMSE-2019), 2019.[Abstract]

Waveriders are of great importance for high speed aircrafts as they offer the promise of greater Lift to Drag (L/D) ratio than generic hypersonic vehicles. A waverider is characterized by a shock wave attached to its leading edge which creates a high- pressure zone under the lower surface, thus allowing for a higher L/D. The present work deals with the analysis of the configuration of the hypersonic Brazilian 14-X waverider. The computational model is generated and the CFD analysis is done in ANSYS FLUENT. The parametric study involves the computation of the maximum lift-to- drag ratio for different Mach number ranging from 6 to 10 and the effect of angle of attack ranging from 0° to 15°. The dependence of the angle of attack (AoA) and the variation of Mach number of the flight with the L/D ratio along with the interdependence of these parameters are studied. The pressure and velocity contour of the model at different values of Mach numbers, AoA and altitudes are noted. The present model for the waverider is found to be efficient at the Mach number 6 at an angle of attack of around 6°.

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S. Shali, Nagaraja, S. R., and Jafarali, P., “Analysis of natural frequency using Differential transform Method”, in International Multi Conference on Innovations in Engineering and Technology, 2014.

Publication Type: Conference Proceedings

Year of Publication Title


H. Venkates, S. Shali, Pillai, H., Venkatesan, H., and Sudhakaran, A., “Parametric Analysis of Waverider in Hypersonic Flow”, AIP Conference Proceedings 2200, 020047 . Effotel Hotel, Indore, 2019.


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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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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Publication Type: Journal Article

Year of Publication Title


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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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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Courses Taught

  • Engineering Mechanics
  • Mechanics of Solids
  • Engineering drawing
  • Dynamics
  • Fluid mechanics and Machinery
  • Theory of Elasticity
  • Mechanical Vibrations
  • Introduction to finite element methods
  • Numerical Methods
  • Environmental Science

Student Guidance

Undergraduate students

Sl. No.

Name of the Student(s)



Year of Completion


J S Chaitanya, Arun Prasad, B Pradeep, PLN SriHarsha

Vibrational Characteristics of AGARD 445.6 Wing in transonic flow


June 2017


Hari Venkates, Harish Pillai, Hemanth Venkatesan, Akshay Sudhakaran

Parametric analysis of waverider in

hypersonic flow


June 2018


Sumanth Pai, Powell Poly Chandy, R. A. Krishnan,

2D analysis of waverider in hypersonic flow


June 2019


Sukruthi C, Aarushi Raghavendra, Ashika


Analysis of subsonic flow over delta winged aircraft


June 2020


V N Vaishak, Soumith Reddy M

Aerodynamic analysis of super critical airfoil


June 2020