Equations of Fluid Motion, Equation of conservation of mass for control volume, special form of e... more Equations of Fluid Motion, Equation of conservation of mass for control volume, special form of equation of conservation of mass, differential form of equation of conservation of mass Euler's and Navier-Stoke equations. Derivation of Bernoulli’s equation for invisid and viscous flow fields. Momentum equation and angular momentum equation in integral form.
Invisid-Incompressible Flow Condition on velocity for incompressible flow. Laplace's equations. P... more Invisid-Incompressible Flow Condition on velocity for incompressible flow. Laplace's equations. Potential function, stream function. Basic elementary flows: Uniform flows, source flow, Doublet flow and Vortex flow. Superimposition of elementary flows. Non lifting and lifting flow over a circular cylinder, comparison with real flow over circular cylinder. Kutta-Jaukowski theorem, generation of lift.
Non-lifting Flow over a Circular Cylinder, Vortex Flow, Lifting Flow over a Cylinder, The Kutta-J... more Non-lifting Flow over a Circular Cylinder, Vortex Flow, Lifting Flow over a Cylinder, The Kutta-Joukowski Theorem and the Generation of Lift. The Flow over a Circular Cylinder—The Real Case. D’ Alembert Paradox, Magnus effects.
Description of Fluid Motion Lagrangian and Eulerian methods, Description of properties in a movin... more Description of Fluid Motion Lagrangian and Eulerian methods, Description of properties in a moving fluid, local and material rate of change. Streamlines, Pathlines, Streaklines, Reynolds Transport theorem, Vorticity and circulation. Laws of vortex motion. Translation, rotation and rate of deformation of fluid particles.
The author expresses profound appreciation to several reference sources for their invaluable aid,... more The author expresses profound appreciation to several reference sources for their invaluable aid, both in both explicit and implicit ways, throughout the composition of this academic work out. In case any correction/s please bring it to Authors Notice. Unit 1 Introduction Fluid statics, pascal’s law,Continuum and free molecular flows, invisid and viscous flows, incompressible and compressible flows. Newtonian and Non-Newtonian flows. Pitot static tube measurement of air-speed, pressure coefficient. Aerodynamic force and moments. Dimensional analysis, non-dimensional parameters, M, Re, Fr etc., flow similarity.
The author expresses profound appreciation to several reference sources for their invaluable aid,... more The author expresses profound appreciation to several reference sources for their invaluable aid, both in both explicit and implicit ways, throughout the composition of this academic work out.
Classification of quasilinear partial differential equations by Cramer’s
rule and eigen value met... more Classification of quasilinear partial differential equations by Cramer’s rule and eigen value method. General behaviour of different classes of partial differential equations and their importance in understanding physical and CFD aspects of aerodynamic problems at different Mach numbers involving hyperbolic, parabolic and elliptic equations- domain of dependence and range of influence for hyperbolic equations. Wellposed problems. Note : Compiled Notes and Material
Aerodynamics during Earth entry, is developed and used for an Ea force of angle of panel is obtai... more Aerodynamics during Earth entry, is developed and used for an Ea force of angle of panel is obtained by Aerodynamic stability Major aspect is to check the lim the spacecraft in longitudinal mode.
The nozzle of the AWJ machine is a critical component which has direct influence on the jet force... more The nozzle of the AWJ machine is a critical component which has direct influence on the jet force developed. In the present scenario, commercially available nozzles have conical section followed by focus section. The critical section is where the cross section of the nozzle changes from conical to straight and suffers severe wall shears stress leading to flow loss. In considering this, computational analysis has been carried on the jet flow through AWJ nozzle with different nozzle geometries. The geometric variation of nozzle profiles show that, reduction in radius of curvature (radius 20 mm) of nozzle geometry produced higher jet velocity and force, as well as lower pressure drop compared to other geometric dimensions.
Equations of Fluid Motion, Equation of conservation of mass for control volume, special form of e... more Equations of Fluid Motion, Equation of conservation of mass for control volume, special form of equation of conservation of mass, differential form of equation of conservation of mass Euler's and Navier-Stoke equations. Derivation of Bernoulli’s equation for invisid and viscous flow fields. Momentum equation and angular momentum equation in integral form.
Invisid-Incompressible Flow Condition on velocity for incompressible flow. Laplace's equations. P... more Invisid-Incompressible Flow Condition on velocity for incompressible flow. Laplace's equations. Potential function, stream function. Basic elementary flows: Uniform flows, source flow, Doublet flow and Vortex flow. Superimposition of elementary flows. Non lifting and lifting flow over a circular cylinder, comparison with real flow over circular cylinder. Kutta-Jaukowski theorem, generation of lift.
Non-lifting Flow over a Circular Cylinder, Vortex Flow, Lifting Flow over a Cylinder, The Kutta-J... more Non-lifting Flow over a Circular Cylinder, Vortex Flow, Lifting Flow over a Cylinder, The Kutta-Joukowski Theorem and the Generation of Lift. The Flow over a Circular Cylinder—The Real Case. D’ Alembert Paradox, Magnus effects.
Description of Fluid Motion Lagrangian and Eulerian methods, Description of properties in a movin... more Description of Fluid Motion Lagrangian and Eulerian methods, Description of properties in a moving fluid, local and material rate of change. Streamlines, Pathlines, Streaklines, Reynolds Transport theorem, Vorticity and circulation. Laws of vortex motion. Translation, rotation and rate of deformation of fluid particles.
The author expresses profound appreciation to several reference sources for their invaluable aid,... more The author expresses profound appreciation to several reference sources for their invaluable aid, both in both explicit and implicit ways, throughout the composition of this academic work out. In case any correction/s please bring it to Authors Notice. Unit 1 Introduction Fluid statics, pascal’s law,Continuum and free molecular flows, invisid and viscous flows, incompressible and compressible flows. Newtonian and Non-Newtonian flows. Pitot static tube measurement of air-speed, pressure coefficient. Aerodynamic force and moments. Dimensional analysis, non-dimensional parameters, M, Re, Fr etc., flow similarity.
The author expresses profound appreciation to several reference sources for their invaluable aid,... more The author expresses profound appreciation to several reference sources for their invaluable aid, both in both explicit and implicit ways, throughout the composition of this academic work out.
Classification of quasilinear partial differential equations by Cramer’s
rule and eigen value met... more Classification of quasilinear partial differential equations by Cramer’s rule and eigen value method. General behaviour of different classes of partial differential equations and their importance in understanding physical and CFD aspects of aerodynamic problems at different Mach numbers involving hyperbolic, parabolic and elliptic equations- domain of dependence and range of influence for hyperbolic equations. Wellposed problems. Note : Compiled Notes and Material
Aerodynamics during Earth entry, is developed and used for an Ea force of angle of panel is obtai... more Aerodynamics during Earth entry, is developed and used for an Ea force of angle of panel is obtained by Aerodynamic stability Major aspect is to check the lim the spacecraft in longitudinal mode.
The nozzle of the AWJ machine is a critical component which has direct influence on the jet force... more The nozzle of the AWJ machine is a critical component which has direct influence on the jet force developed. In the present scenario, commercially available nozzles have conical section followed by focus section. The critical section is where the cross section of the nozzle changes from conical to straight and suffers severe wall shears stress leading to flow loss. In considering this, computational analysis has been carried on the jet flow through AWJ nozzle with different nozzle geometries. The geometric variation of nozzle profiles show that, reduction in radius of curvature (radius 20 mm) of nozzle geometry produced higher jet velocity and force, as well as lower pressure drop compared to other geometric dimensions.
Automotive chassis design, development is quite important in today’s environment. This work is or... more Automotive chassis design, development is quite important in today’s environment. This work is oriented towards analysis of a ladder chassis and space frame chassis design. The analysis of the designed models involves the use of three different materials. In this investigation two different conditions of vehicle loading are considered namely un-laden (without passengers that is the KERB weight of the vehicle) condition and the laden (with passengers and miscellaneous weight also called gross weight) condition. Analysis had resulted with various variables of stress indicating the stress levels minimum in unladen case as 3.00E-17 and maximum in laden case as 29.8662, in case of space frame analysis the stress in minimum for steel with laden chasis as 0.001558 and maximum in case of composite material as 7.8447. These results would be useful with in selection of material for automotive frames
The nozzle of the AWJ machine is a critical component which has direct influence on the jet force... more The nozzle of the AWJ machine is a critical component which has direct influence on the jet force developed. In the present scenario, commercially available nozzles have conical section followed by focus section. The critical section is where the cross section of the nozzle changes from conical to straight and suffers severe wall shears stress leading to flow loss. In considering this, computational analysis has been carried on the jet flow through AWJ nozzle with different nozzle geometries. The geometric variation of nozzle profiles show that, reduction in radius of curvature (radius 20 mm) of nozzle geometry produced higher jet velocity and force, as well as lower pressure drop compared to other geometric dimensions.
Graduate Research in Engineering and Technology, 2022
High Altitude Long Endurance Unmanned Aerial Vehicles (HALE UAVs) could provide an improved servi... more High Altitude Long Endurance Unmanned Aerial Vehicles (HALE UAVs) could provide an improved service and/or flexibility at a reduced cost over existing systems for a vast number of civil patrol and surveillance applications. This document looks into the Feasibility and Conceptual Design of Solar Powered UAV for HALE applications. It mentions the advancements in technology of the components required to build an efficient solar powered UAV. It also provides a preliminary design methodology that can be adopted for the conceptual design of Solar Powered UAV. It also emphasizes the Aerodynamic difficulties that are faced in HALE configurations.
Computational analysis is carried out on Hypersonic Vehicle intake configuration at free stream m... more Computational analysis is carried out on Hypersonic Vehicle intake configuration at free stream mach numbers of 3.0, 3.5 and 3.9 through commercial software CFD ANSYS-CFX. The purpose of this study is to ascertain the starting of intake at higher contraction ratio using the concept of variable geometry and also to evaluate the performance of the intake in terms of pressure and mach number of the flow entering the diffuser/combustion chamber. The variable geometry is achieved by attaching a flap to the intake. The investigation is carried out based on flap angle variation at different free stream machnumbers and to identify a feasible range of inlet operations.
The main objective of this study is to increase the aerodynamic efficiency of turbine mounted nov... more The main objective of this study is to increase the aerodynamic efficiency of turbine mounted novel wing. The main motive behind this work is to reduce the drag by attaining the positive velocity gradient and generate power by converting the stagnation pressure which also acts as emergency power source. By using the energy source of free stream air, Mechanical energy is converted into electrical energy. The obtained power is presented in terms of voltage generated at various angles of attack with different Reynolds number. Experimental analysis is carried out for NACA4415 airfoil at various angles with respect to free stream ranging from 0deg to 30deg from laminar to turbulent Reynolds number. The results were obtained using the research tunnel at IARE aerodynamic facility center. The aerodynamic advantage of this design in terms of voltage is 9.5 V at 35m/s which can be utilized for the aircraft on board power systems.
Automotive chassis design, development is quite important in today's environment. This work is or... more Automotive chassis design, development is quite important in today's environment. This work is oriented towards analysis of a ladder chassis and space frame chassis design. The analysis of the designed models involves the use of three different materials. In this investigation two different conditions of vehicle loading are considered namely unladen (without passengers that is the KERB weight of the vehicle) condition and the laden (with passengers and miscellaneous weight also called gross weight) condition. Analysis had resulted with various variables of stress indicating the stress levels minimum in unladen case as 3.00E-17 and maximum in laden case as 29.8662, in case of space frame analysis the stress in minimum for steel with laden chasis as 0.001558 and maximum in case of composite material as 7.8447. These results would be useful with in selection of material for automotive frames.
A dynamic wedge: use of a computer controlled dose distribution generation technique for simulati... more A dynamic wedge: use of a computer controlled dose distribution generation technique for simulation of wedge filters on a teletherapy treatment unit Abstract. Aeronautical studies are being focused more towards supersonic flights and methods to attain a better and safer flight with highest possible performance. Aerodynamic analysis is part of the whole procedure, which includes focusing on airfoil shapes which will permit sustained flight of aircraft at these speeds. Airfoil shapes differ based on the applications, hence the airfoil shapes considered for supersonic speeds are different from the ones considered for Subsonic. The present work is based on the effects of change in physical parameter for the Double wedge airfoil. Mach number range taken is for transonic and supersonic. Physical parameters considered for the Double wedge case with wedge angle (ranging from 5 degree to 15 degree. Available Computational tools are utilized for analysis. Double wedge airfoil is analysed at different Angles of attack (AOA) based on the wedge angle. Analysis is carried out using fluent at standard conditions with specific heat ratio taken as 1.4. Manual calculations for oblique shock properties are calculated with the help of Microsoft excel. MATLAB is used to form a code for obtaining shock angle with Mach number and wedge angle at the given parameters. Results obtained from manual calculations and fluent analysis are cross checked.
The nozzle of the AWJ machine is a critical component which has direct influence on the jet force... more The nozzle of the AWJ machine is a critical component which has direct influence on the jet force developed. In the present scenario, commercially available nozzles have conical section followed by focus section. The critical section is where the cross section of the nozzle changes from conical to straight and suffers severe wall shears stress leading to flow loss. In considering this, computational analysis has been carried on the jet flow through AWJ nozzle with different nozzle geometries. The geometric variation of nozzle profiles show that, reduction in radius of curvature (radius 20 mm) of nozzle geometry produced higher jet velocity and force, as well as lower pressure drop compared to other geometric dimensions.
The present study emphasizes on interaction between the lifting structure and the fluid flow i.e.... more The present study emphasizes on interaction between the lifting structure and the fluid flow i.e. submerged flow a wing results in various dynamic phenomenal changes. The traditional analysis of a flow field around a finite wing assumes that the lifting body is rigid and doesn't experience any deformation. This study utilizes fluid structure interaction principles to compute and define the structural stability of the modern aircraft wings namely Cessna 172, Boeing 737 and Glaser-dirks dg-808 glider. The above aircrafts have been considered due to their unique wing design and diversified characteristics. The study has been conducted using the commercial software ANSYS Inc. and the results will be presented based on Fluid Structure Interaction in the context of aerodynamic behaviour of the wing.
— Functionally Graded Materials (FGM) have continuous variation of material properties from one s... more — Functionally Graded Materials (FGM) have continuous variation of material properties from one surface to another. The gradation of properties in an FGM reduces the thermal stresses, residual stresses, and stress concentrations found in traditional composites. This paper will explore analysis of FGM flat plates under pressure i.e. mechanical loading in order to understand the effect variation of material properties has on structural response. Theoretical formulation of various material properties is done using Rule of mixtures. The plate is then modeled and subjected to specific boundary conditions after which analysis is carried out. The convergence studies with respect to varying mesh and layers are carried out in order to obtain accurate results. Having fixed a mesh size and number of layers, the variation of displacements and stresses through the thickness of the plate is studied. In addition to this, the variation of the same parameters with changing volume fraction of ceramic is also understood. Results are compared to published results in order to show the accuracy of modelling FGMs using ANSYS software.
Propulsion Classification and essential features of propulsion, jet propulsion, general character... more Propulsion Classification and essential features of propulsion, jet propulsion, general characteristics of rocket engines, theory of propulsion, elementary gas dynamics, spacecrafts and aircraft performance.
Anatomy of flight vehicles, components of an airplanes and their function, configuration of space... more Anatomy of flight vehicles, components of an airplanes and their function, configuration of space vehicle, earth's atmosphere and gravitational field, bluff bodies v/s streamlined body, airfoil. lift generation, significance of L/D ratio, aerodynamic forces, pressure, Actual and theoretical PV diagrams of four stroke and two stroke IC Engines.
History of aviation, early development of airplanes, biplanes and monoplanes, history of spacefli... more History of aviation, early development of airplanes, biplanes and monoplanes, history of spaceflight, development of space vehicle, classification of duct jet propulsion, rocket propulsion, advance propulsion and applications
Basic laws for a system in integral form: Reynolds transport theorem, Conservation of mass, Newto... more Basic laws for a system in integral form: Reynolds transport theorem, Conservation of mass, Newton‘s 2nd law; Application of the basic laws for a control volume; Kinematics; Motion of a fluid particle; Fluid deformation; Differential analysis of fluid motion: Continuity equation, Differential momentum equation, Surface and body forces, substantive derivative, local derivative and convective derivative, momentum equation, Euler's and Bernoulli's equation, phenomenological basis of Naviers- stokes equation, introduction to vortex flows, flow measurements : pressure, velocity and mass flow rate, viscosity, pivot-static tube, venture meter and orifice meter, viscometers. Statement of Buckingham‘s π- theorem, similarity parameters - Reynolds number, Froude number, concepts of geometric, kinematic and dynamic similarity, Reynolds number as a very approximate measure of ratio of inertia force and viscous force.
Boundary layer - introductory concepts of boundary layer, large Reynolds number flows and Prandtl... more Boundary layer - introductory concepts of boundary layer, large Reynolds number flows and Prandtl‘s boundary layer hypothesis Pressure drag and skin friction drag; Pipe flow - Reynolds experiment, Darcy‘s equation, major and minor losses in pipes and numerical problems. Flow between parallel plates, flow through long tubes –fully developed flow, Turbulent flow, variation of friction factor with Reynolds‘s Number, Moody's chart.
Introduction and classification of fluid machines: Turbo machinery analysis; The angular momentum... more Introduction and classification of fluid machines: Turbo machinery analysis; The angular momentum principle; Euler turbo machine equation; Velocity triangles; Application to fluid systems - Working principle overview of turbines, fans, pumps and compressors.
Ground testing and flight testing- types of tests, test facilities and safeguards, monitoring and... more Ground testing and flight testing- types of tests, test facilities and safeguards, monitoring and control of toxic materials, instrumentation and data management. Ground testing, flight testing, trajectory monitoring, post accident procedures. Description of a typical space launch vehicle launches procedure.
Propagation of sound waves through compressible fluids, Sonic velocity
and Mach number; Applicati... more Propagation of sound waves through compressible fluids, Sonic velocity and Mach number; Application of continuity, momentum and energy equations for steady state conditions; steady flow through nozzle, Effect of varying back pressure on nozzle performance, Critical pressure ratio Normal shocks, basic equations of normal shock, change of properties across normal shock.
Boundary Layer: Concept of boundary layer and definition of boundary
layer thickness, displacemen... more Boundary Layer: Concept of boundary layer and definition of boundary layer thickness, displacement, momentum and energy thickness; Growth of boundary layer, laminar and turbulent boundary layers, laminar sub-layer; Von Karman Momentum Integral equation for boundary layers, analysis of laminar and turbulent boundary layers, drag, boundary layer separation and methods to control it, streamlined and bluff bodies
Fluid Dynamics: Surface & body forces, substantive derivative, local derivative and convective de... more Fluid Dynamics: Surface & body forces, substantive derivative, local derivative and convective derivative, momentum equation, Euler equation, Bernoulli’s equation Similarity parameters: Reynolds number, Froude number, Concepts of geometric, kinematic and dynamic similarity, Viscous Force Flow measurements: pressure, velocity and mass flow rate, viscosity, Pitot-static tube, venturi meter and orifice meters, viscometers. Reynolds experiment, Darcy’s equation, major and minor losses in pipes and numerical problems.
Fluid Properties: Density, specific weight, specific gravity, surface tension & capillarity, Newt... more Fluid Properties: Density, specific weight, specific gravity, surface tension & capillarity, Newton’s law of viscosity, incompressible & compressible fluid, numerical problems. Hydrostatic forces on submerged bodies: Pressure at a point, Pascal’s law, pressure variation with temperature and height, Center of pressure on vertical, inclined and curved surfaces. Manometers-simple and differential manometers, inverted manometers, micro manometers, Pressure gauges and numerical problems. Buoyancy-Archimedes’ Principle, Metacenter, metacentric height calculations.
Critical Mach number & Drag Divergence, drag reduction & lift
augmentation – Sweep, winglets, Fla... more Critical Mach number & Drag Divergence, drag reduction & lift augmentation – Sweep, winglets, Flaps, slats and vortex generators. Propellers: Concept of slip stream with only axial velocity, Actuator disk theory due to Rankine & Froude; power & thrust coefficients, propeller twist blade element analysis , blade angle, advance ratio and Torque coefficient , efficiency , propeller charts.
Vortex filament statement of Helmholtz's vortex theorems, Biot-Savart Law, starting, bound & trai... more Vortex filament statement of Helmholtz's vortex theorems, Biot-Savart Law, starting, bound & trailing vortices of wings, Lanchester's experiment, Prandtl's Lifting line theory-downwash and induced drag, Elliptic loading & wings of elliptic platforms, expression for induced drag, minimum induced drag for Elliptic platform. Source and vortex panel methods for airfoils. Replacement of an airfoil by a concentrated vortex at quarter-chord point, importance of three-quarter chord point for discretization, use of quarter chord and three-quarter chord points in vortex panel method for wings.
Course: Aerodynamics I Unit III : Viscous Flow and Boundary Layer Lecture : I Course Outcomes: At... more Course: Aerodynamics I Unit III : Viscous Flow and Boundary Layer Lecture : I Course Outcomes: At the end of the course, student should be able to, CLO 1 Learn Fundamentals of rocket and missile systems, functions and disciplines and the full spectrum of rocket systems, uses and technologies. CLO 2 Understand the Fundamentals and uses of solid, liquid and hybrid rocket systems and differences between systems built as weapons and those built for commerce. CLO 3 Knowledge of forces acting on missiles and considerations of design in different phases. CLO 4 Explain the use of low and high-fidelity performance modelling, including performance loss factors, Staging theory, performance and practices for multi-stage rockets. CLO 5 Understand the concept of testing of rockets and data management techniques.
Rocket thrust vector control methods of thrust vector control for solid
and liquid propulsion sys... more Rocket thrust vector control methods of thrust vector control for solid and liquid propulsion systems, thrust magnitude control, thrust termination Stage separation dynamics, separation techniques Tsiolskovsky’s rocket equation range in the absence of gravity, vertical motion in the earth’s gravitational field, inclined motion, flight path at constant pitch angle, motion in the atmosphere, the gravity turn the culmination altitude Multi staging Earth launch trajectories vertical segment, the gravity turn, constant pitch trajectory, orbital injection
Course: Missile Aerodynamics Unit III : Aerodynamics of Rockets And Missiles Lecture : I Course O... more Course: Missile Aerodynamics Unit III : Aerodynamics of Rockets And Missiles Lecture : I Course Outcomes: At the end of the course, student should be able to, CLO 1 Learn Fundamentals of rocket and missile systems, functions and disciplines and the full spectrum of rocket systems, uses and technologies. CLO 2 Understand the Fundamentals and uses of solid, liquid and hybrid rocket systems and differences between systems built as weapons and those built for commerce. CLO 3 Knowledge of forces acting on missiles and considerations of design in different phases. CLO 4 Explain the use of low and high-fidelity performance modelling, including performance loss factors, Staging theory, performance and practices for multi-stage rockets. CLO 5 Understand the concept of testing of rockets and data management techniques.
Gasturbinesusedinaircraftareoperatedinavarietyofenvironmentsrangingfromarctictodesertconditions.D... more Gasturbinesusedinaircraftareoperatedinavarietyofenvironmentsrangingfromarctictodesertconditions.Desertareaspresentaparticularchallengetogasturbineoperationbecauseofparticulatematterthatcanbeingestedintotheengine,whentheengineoperatesneargroundlevel.Predictionsofparticulateladenflowswiththeaccountofturbulentviscousfluidsarecomplexphysicsandcanbeapproachedintwoways–Onewayortwowaycoupling.
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equations. Derivation of Bernoulli’s equation for invisid and viscous flow fields. Momentum equation and angular momentum equation in
integral form.
Unit 1
Introduction Fluid statics, pascal’s law,Continuum and free molecular flows, invisid and viscous flows, incompressible and compressible flows. Newtonian and Non-Newtonian flows. Pitot static tube measurement of air-speed, pressure coefficient. Aerodynamic force and moments. Dimensional analysis, non-dimensional parameters, M, Re, Fr etc., flow similarity.
Pressure distribution over smooth and rough cylinder.
Pressure distribution over symmetric airfoil
Pressure distribution over cambered airfoil & thin airfoils
Force measurement using wind tunnel balance.
Flow over a flat plate at different angles of incidence
Flow visualization over cylinder
Flow visualization studies in low-speed flow over airfoil with different angle of incidence
rule and eigen value method. General behaviour of different classes of
partial differential equations and their importance in understanding
physical and CFD aspects of aerodynamic problems at different Mach
numbers involving hyperbolic, parabolic and elliptic equations- domain
of dependence and range of influence for hyperbolic equations.
Wellposed problems.
Note : Compiled Notes and Material
equations. Derivation of Bernoulli’s equation for invisid and viscous flow fields. Momentum equation and angular momentum equation in
integral form.
Unit 1
Introduction Fluid statics, pascal’s law,Continuum and free molecular flows, invisid and viscous flows, incompressible and compressible flows. Newtonian and Non-Newtonian flows. Pitot static tube measurement of air-speed, pressure coefficient. Aerodynamic force and moments. Dimensional analysis, non-dimensional parameters, M, Re, Fr etc., flow similarity.
Pressure distribution over smooth and rough cylinder.
Pressure distribution over symmetric airfoil
Pressure distribution over cambered airfoil & thin airfoils
Force measurement using wind tunnel balance.
Flow over a flat plate at different angles of incidence
Flow visualization over cylinder
Flow visualization studies in low-speed flow over airfoil with different angle of incidence
rule and eigen value method. General behaviour of different classes of
partial differential equations and their importance in understanding
physical and CFD aspects of aerodynamic problems at different Mach
numbers involving hyperbolic, parabolic and elliptic equations- domain
of dependence and range of influence for hyperbolic equations.
Wellposed problems.
Note : Compiled Notes and Material
and Mach number; Application of continuity, momentum and
energy equations for steady state conditions; steady flow through
nozzle, Effect of varying back pressure on nozzle performance, Critical
pressure ratio Normal shocks, basic equations of normal shock, change
of properties across normal shock.
layer thickness, displacement, momentum and energy thickness;
Growth of boundary layer, laminar and turbulent boundary layers,
laminar sub-layer; Von Karman Momentum Integral equation for
boundary layers, analysis of laminar and turbulent boundary layers,
drag, boundary layer separation and methods to control it, streamlined
and bluff bodies
Similarity parameters: Reynolds number, Froude number, Concepts of geometric, kinematic and dynamic similarity, Viscous Force
Flow measurements: pressure, velocity and mass flow rate, viscosity, Pitot-static tube, venturi meter and orifice meters, viscometers. Reynolds experiment, Darcy’s equation, major and minor losses in pipes and numerical problems.
augmentation – Sweep, winglets, Flaps, slats and vortex generators.
Propellers: Concept of slip stream with only axial velocity, Actuator disk
theory due to Rankine & Froude; power & thrust coefficients, propeller
twist blade element analysis , blade angle, advance ratio and Torque
coefficient , efficiency , propeller charts.
and liquid propulsion systems, thrust magnitude control, thrust
termination Stage separation dynamics, separation techniques
Tsiolskovsky’s rocket equation range in the absence of gravity, vertical
motion in the earth’s gravitational field, inclined motion, flight path at
constant pitch angle, motion in the atmosphere, the gravity turn the
culmination altitude Multi staging Earth launch trajectories vertical
segment, the gravity turn, constant pitch trajectory, orbital injection
Liquid propellants types, composition, properties, performance Propellant tanks feed systems pressurisation turbo pumps valves and feed lines, injectors starting and ignition Engine cooling, support structure Control of engine starting and thrust build up.