Aerodynamic
aerodynamic
Syllabus
Faculty: Dr. Sangram Samal
To make the student understand the 2-D flow ideal and real flow.
To make the student understand the concept of viscous flow.
To make the student understand the deferent types of drag.
To make the student understand the compressible effect over wing.
Using Dassault system
Compare the CFD data with experimental and analyzing
Ability to estimate aircraft drag (low speed & high speed)
Understanding of sensitivity of aircraft drag to various aircraft parameters
Module I: Two dimensional Flow (4hrs)
Pressure and velocity distributions on bodies with and without circulation in ideal and real fluid flows. Kutta Joukowski’s theorem. D’Alembert Paradox, Magnus effects.
Practice-Pressure distribution over cylinder with and without circulation using Dassault systemes
Simulate the pressure around fuselage using Dassault systemes
Module II: Viscous Flow ( 5 hrs)
Reynolds number, laminar flow, transition flow and turbulent flow, Boundary layer and boundary layer thickness, displacement thickness, momentum thickness, Energy thickness,
Practice- Flow over a flat plate at different Reynolds no using Dassault systemes.
Module III: Flow separation and control techniques (4 hrs)
Boundary Layer growth and point of separation, Techniques to control the point of separation, Flow over different contours.
Practice- Flow over a flat plate at different angles of incidence using Dassault systemes.
Module IV: Aerodynamics Drag (4 hrs)
Aerodynamics parameter, Wing tip vortex, down wash, different types of drag method to minimizing those. Aerodynamic efficiency and dependency,
Practice- Compare the Lift, drag and aerodynamic efficiency at different angle of attack of an airfoil using Dassault systemes and wind tunnel.
Practice- Design and simulate nacelles, intakes and nozzles using Dassault system
Module V: Shock Wave ( 4 hrs)
Normal shock and equations, Oblique shocks and corresponding equations, θ- β- M relation, Hodograph and pressure turning angle, shock polar, flow past wedges. strong, weak and detached shocks .
Practice- Design and simulate the flow over nacelles, intakes and nozzles using Dassault system
Module VI: Expansion Waves, Rayleigh And Fanno Flow (5hrs)
Rayleigh and Fanno Flow. Flow past convex corners, Expansion hodograph, Reflection and interaction of shocks and expansion waves, Methods of Characteristics, Two dimensional supersonic nozzle contours.
Practice- Find out pressure and velocity distribution in high speed jet using Dassault systemes also using experimental and compare the results.
Module VII: Airfoil in High Speed Flows (4hrs)
Critical Mach numbers, Lift and drag divergence, Characteristics of swept wings, Effects of thickness, camber and aspect ratio of wings, Transonic area rule, Tip effects.
Practice- Design the different swept back wing and check the effect on transonic speed using Dassault systemes
Pressure and velocity distributions over a cylinder without circulation in ideal flow and real flow.
Kutta Joukowski’s theorem
Kutta
D’Alembert Paradox, Magnus effects.
https://www.youtube.com/watch?v=4BSgDJ6dwEM
https://www.youtube.com/watch?v=2OSrvzNW9FE
magnuseffect
Practice- Pressure distribution over cylinder with and without circulation using Dassault systemes
laminar flow, transition flow and turbulent flow
https://www.youtube.com/watch?v=56AyTIhNQBo
https://www.youtube.com/watch?v=1wNmtle6qkE
Reynolds number and effect on aerodynamics parameters
Boundary layer and boundary layer thickness
Boundary Layer
displacement thickness
momentum thickness and Energy thickness
Practice-
Flow over a flat plate at different Reynolds no usingDassault systemes.
Boundary Layer growth and point of separation
Boundary Layer separation
Techniques to control the point of separation
https://www.youtube.com/watch?v=Sw-K3Z7GgdE
Flow over different contours
Practice-
Flow over a flat plate at different angles of incidence using Dassault systemes.
Aerodynamics parameters and uses
Wing tip vortex, down wash
https://www.youtube.com/watch?v=E1ESmvyAmOs
different types of drag method to minimizing those
Drag
Drag1
Compare the Lift, drag and aerodynamic efficiency at different angle of attack of an airfoil using Dassault systemes and wind tunnel.
Normal shock
https://www.youtube.com/watch?v=ng4XMEWUCLI
Oblique shocks
θ- β- M relation
Hodograph and pressure turning angle
shock polar, flow past wedges.
strong, weak and detached shocks .
https://www.youtube.com/watch?v=ng4XMEWUCLI&t=269s
Practice- Design and simulate the flow over nacelles, intakes and nozzles using Dassault system
Rayleigh and Fanno Flow.
Flow past convex corners, Expansion hodograph
Reflection and interaction of shocks and expansion waves
Methods of Characteristics, Two dimensional supersonic nozzle contours.
Practice- Find out pressure and velocity distribution in high speed jet using Dassault systemes also using experimental and compare the results.
Critical Mach numbers
https://www.youtube.com/watch?v=SgolxnDFL48
Lift and drag divergence
Lift and drag divergence
Area rule, Characteristics of swept wings
arearule
Characteristics of swept wings
https://www.youtube.com/watch?v=qyw6H6HVRro
Effects of thickness, camber
Tip effects and Aspect Ratio on critical mach no
Practice- Design the different swept back wing and check the effect on transonic speed using Dassault systemes
Course Name : Aerodynamic
Code(Credit) : CUTM1096(3-1-0)
Course Objectives
To make the student understand the 2-D flow ideal and real flow.
To make the student understand the concept of viscous flow.
To make the student understand the deferent types of drag.
To make the student understand the compressible effect over wing.
Learning Outcomes
Using Dassault system
Compare the CFD data with experimental and analyzing
Ability to estimate aircraft drag (low speed & high speed)
Understanding of sensitivity of aircraft drag to various aircraft parameters
Course Syllabus
Module I: Two dimensional Flow (4hrs)
Pressure and velocity distributions on bodies with and without circulation in ideal and real fluid flows. Kutta Joukowski’s theorem. D’Alembert Paradox, Magnus effects.
Practice-Pressure distribution over cylinder with and without circulation using Dassault systemes
Simulate the pressure around fuselage using Dassault systemes
Module II: Viscous Flow ( 5 hrs)
Reynolds number, laminar flow, transition flow and turbulent flow, Boundary layer and boundary layer thickness, displacement thickness, momentum thickness, Energy thickness,
Practice- Flow over a flat plate at different Reynolds no using Dassault systemes.
Module III: Flow separation and control techniques (4 hrs)
Boundary Layer growth and point of separation, Techniques to control the point of separation, Flow over different contours.
Practice- Flow over a flat plate at different angles of incidence using Dassault systemes.
Module IV: Aerodynamics Drag (4 hrs)
Aerodynamics parameter, Wing tip vortex, down wash, different types of drag method to minimizing those. Aerodynamic efficiency and dependency,
Practice- Compare the Lift, drag and aerodynamic efficiency at different angle of attack of an airfoil using Dassault systemes and wind tunnel.
Practice- Design and simulate nacelles, intakes and nozzles using Dassault system
Module V: Shock Wave ( 4 hrs)
Normal shock and equations, Oblique shocks and corresponding equations, θ- β- M relation, Hodograph and pressure turning angle, shock polar, flow past wedges. strong, weak and detached shocks .
Practice- Design and simulate the flow over nacelles, intakes and nozzles using Dassault system
Module VI: Expansion Waves, Rayleigh And Fanno Flow (5hrs)
Rayleigh and Fanno Flow. Flow past convex corners, Expansion hodograph, Reflection and interaction of shocks and expansion waves, Methods of Characteristics, Two dimensional supersonic nozzle contours.
Practice- Find out pressure and velocity distribution in high speed jet using Dassault systemes also using experimental and compare the results.
Module VII: Airfoil in High Speed Flows (4hrs)
Critical Mach numbers, Lift and drag divergence, Characteristics of swept wings, Effects of thickness, camber and aspect ratio of wings, Transonic area rule, Tip effects.
Practice- Design the different swept back wing and check the effect on transonic speed using Dassault systemes
Text Books:
Clancey, L.J., “Aerodynamics”,
Anderson Jr., D., ‐ "Modern compressible flows", McGraw‐Hill Book Co., New York 2012.
Reference Books:
Rathakrishnan, E., "Gas Dynamics", Prentice Hall of India, 2012. Anderson, Jr., J.D. Introduction to Flight, McGraw-Hill International Edition, 1999
Session Plan
Session 1
Pressure and velocity distributions over a cylinder without circulation in ideal flow and real flow.
Session 2
Kutta Joukowski’s theorem
Kutta
Session 3
D’Alembert Paradox, Magnus effects.
https://www.youtube.com/watch?v=4BSgDJ6dwEM
https://www.youtube.com/watch?v=2OSrvzNW9FE
magnuseffect
Session 4
Practice- Pressure distribution over cylinder with and without circulation using Dassault systemes
Session 5
laminar flow, transition flow and turbulent flow
https://www.youtube.com/watch?v=56AyTIhNQBo
https://www.youtube.com/watch?v=1wNmtle6qkE
Session 6
Reynolds number and effect on aerodynamics parameters
Session 7
Boundary layer and boundary layer thickness
Boundary Layer
Session 8
displacement thickness
Session 9
momentum thickness and Energy thickness
Session 10
Practice-
Flow over a flat plate at different Reynolds no usingDassault systemes.
Session 11
Boundary Layer growth and point of separation
Boundary Layer separation
Session 12
Techniques to control the point of separation
https://www.youtube.com/watch?v=Sw-K3Z7GgdE
Session 13
Flow over different contours
Session 14
Practice-
Flow over a flat plate at different angles of incidence using Dassault systemes.
Session 15
Aerodynamics parameters and uses
Session 16
Wing tip vortex, down wash
https://www.youtube.com/watch?v=E1ESmvyAmOs
Session 17
different types of drag method to minimizing those
Drag
Drag1
Session 18
Compare the Lift, drag and aerodynamic efficiency at different angle of attack of an airfoil using Dassault systemes and wind tunnel.
Session 19
Normal shock
https://www.youtube.com/watch?v=ng4XMEWUCLI
Session 20
Oblique shocks
Session 21
θ- β- M relation
Session 22
Hodograph and pressure turning angle
Session 23
shock polar, flow past wedges.
Session 24
strong, weak and detached shocks .
https://www.youtube.com/watch?v=ng4XMEWUCLI&t=269s
Session 25
Practice- Design and simulate the flow over nacelles, intakes and nozzles using Dassault system
Session 26
Rayleigh and Fanno Flow.
Session 27
Flow past convex corners, Expansion hodograph
Session 28
Reflection and interaction of shocks and expansion waves
Session 29
Methods of Characteristics, Two dimensional supersonic nozzle contours.
Session 30
Practice- Find out pressure and velocity distribution in high speed jet using Dassault systemes also using experimental and compare the results.
Session 31
Critical Mach numbers
https://www.youtube.com/watch?v=SgolxnDFL48
Session 32
Lift and drag divergence
Lift and drag divergence
Session 33
Area rule, Characteristics of swept wings
arearule
Characteristics of swept wings
https://www.youtube.com/watch?v=qyw6H6HVRro
Session 34
Effects of thickness, camber
Session 35
Tip effects and Aspect Ratio on critical mach no
Session 36
Practice- Design the different swept back wing and check the effect on transonic speed using Dassault systemes
Case Studies
Case Studies
Course Materials
Session plan & materials
No materials published yet.