Education

• Ph.D, Aerospace Engineering, IISc, Bengaluru
• M.E, Space Engineering & Rocketry, BIT, Mesra, Ranchi
• B.Tech, Mechanical Engineering, Calicut University, Kerala

Research Work / Area

• Gas Dynamics, Hypersonic flows, Experimental Aerodynamics

Funded Project

Simulation on non-equilibrium hypersonic flow in shock tunnel nozzle. IIST-ISRO project,2018-19, Satheesh.K(PI), Devendra Ghate(Co-PI)

Development of fast responce TDLAS sensor for high temperature applications, ARDB,2022-25, Rajesh S (PI), Satheesh K(Co-PI)

Assessment of Stability Limits and NOx Emissions of Non-premixed Ammonia- Hydroge/Air Flames, DST-DAAD project,2024-25,Rajesh S (PI), Satheesh K(Co-PI)

Journal Articles

1. Satheesh.K, Jagadeesh.G & Reddy.K.P.J, High speed schlieren facility for visualisation of flow fields in hypersonic shock tunnels, Current science, 92-1, pp.56-60, 2007.
2. Satheesh.K & Jagadeesh.G, Effect of concentrated energy deposition on the aerodynamic drag of a blunt body in hypersonic flow, Physics of fluids, 19-3,  pp.031701-1-4, 2007.
3. Satheesh.K & Jagadeesh.G, Experimental investigations on the effect of energy deposition on hypersonic blunt body flow field, Shock Waves, 18-1, pp.53-70, 2008.
4. Satheesh.K& Jagadeesh.G, Analysis of an internally mountable accelerometer balance systemfor use with non-isotropic models in shock tunnels, Measurement, 42-6, pp.856-862, 2009.

Undergraduate

Introduction to Aerospace Engineering

Aerodyamics

Compressible Flows

Atmospheric Flight Mechanics

Air breathing propulsion (Shared with Dr Prathap)

Aerodynamics Lab

Flight Mechanics Lab

Post Graduate

Introduction to Aerospace Engineering

Mathematical methods for Aerospace Engineering

Fligth Dynamics & Control

 Aerodyamics

Aerodynamics and Flight Mechanics lab

Electives

High Temperature Gas Dynamics

Boundary Layer Theory

Experimental Aerodynamics

IIST Shock tube

This facility is a part of the High speed flow lab at IIST. A shock tube can be used for generating controlled shock waves using which gases can be heated to  high temeperature 
Gas temeperatrues as high as 2200K can be reaslised using the IIST sock tube. Due to its modular design the facility can be operated as a shock tube, supersonic tunnel and a shock tunnel. A Mach 3.5 contoured supersonic nozzle with an optically accessible 2D test section is also available for integration with this facility. The facilty is instrumented with dynamic pressure sesnors,  high speed data acquisition system and a high speed schlieren system.  Ongoing research activities in this lab are listed bleow

• Study of non-ideal effects in shock tube flows
• Development of TDLAS based diagnostics for shock tube
• Unsteady force measuremtns using strain gages

Laser absorption spectroscopy lab

This lab focuses on the development of sensors based on Tunable Diode Laser Absorption Spectroscopy(TDLAS). These non intrusive sensors have a wide range of applicaitons and we
are currently focusing on application to Combustion research, High enthalpy flows and atmospheric sensing.

Tunable DFB diode lasers are used to traget the absorption features os species such as H₂O, O₂ and CH₄ in order to measure the gas temperature and species concentration. The ongoing sensor development work is listed bleow

• HIgh speed TDLAS for shock tube flows
• Trace gas TDLAS sensing with multi-pass cell
• WMS based sensing for high pressure applications

 Collaborators: Rajesh Sadanandan, Asso Prof IIST