SG3113 Compressible Aerodynamics 9.0 credits
The course will primarily be based on selected parts of the book by John D. Andersson, Modern Compressible Flow, Mc Graw Hill , 1990, from which may be cited:
"This book deals exclusively with that "marked departure", i.e., it deals with compressible flows, in which the density is not constant. In modern engineering applications, such flows are the rule rather than the exception. A few important examples are the internal flows through rocket and gas turbine engines, high-speed subsonic, transonic, supersonic, and hypersonic wind tunnels, the external flow over modern airplanes designed to cruise faster than 0.3 of the speed of sound, and the flow inside the common internal combustion reciprocating engine. The purpose of this book is to develop the fundamental concepts of compressible flow, and to illustrate their use."
Education cycleThird cycle
Main field of study
Information for research students about course offerings
Period 4 and 1. See KTH-schedule for undergraduate course
SG2215 and SG2219.
Intended learning outcomes
Finishing this course the student should know how to:
- derive the conservation laws of mass, momentum and energy of inviscid, compressible flow and apply them to various fluid dynamical problems to e.g.
- analyse the interaction of forces between solid boundaries and flowing gases from the basic principles of compressible flow
- analyse the energy conversion process in a flowing gas from the thermodynamic principles of isentropic and irreversible flow respectively
- interpret results from performed experiments
- demonstrate a physical understanding of the mathematical formulas derived
- give a physical description of the special effects appearing in hypersonic flows.
- explain the consequences of the effects of compressibility on the flow in a viscous boundary layer
Course main content
For an inviscid, compressible gas the students should be able to
- calculate pressure, velocity and temperature for quasi one-dimensional, stationary, isentropic flow
- calculate changes of pressure, velocity and temperature over normal and oblique shock waves
- calculate changes of pressure, velocity and temperature in simple expansion waves
- calculate pressure, velocity and temperature for unsteady, one-dimensional, non-linear waves
- calculate the flow field in linear theory for subsonic and supersonic flow around bodies
- understand how pressure and drag on a body changes in transsonic flow
- derive the conservation equations governing the flow of compressible fluids in boundary layers
- derive solutions to the boundary layer equations for some cases demonstrating the main features of compressible flow in a boundary layer
Basic courses at M, P, T or F and one of SG1217, SG1220, SG2223, SG2214 or equivalent courses.
The course assumes that the contents of the course SG1217, SG1220, SG2223 or SG2214, or something similar, have been studied.
Andersson, Modern Compressible Flow, With Historical Perspective, Mc Graw Hill, 2003, ISBN 0-07-242443-5.
Selected paragraphs of: Transition, Turbulence and Combustion modelling, Lecture notes from the 2nd ERCOFTAC Summerschool held in Stockholm, 10-16 June, 1998. Edited by A. Hanifi, P.H. Alfredsson, A.V. Johansson and D.S. Henningsson.
Requirements for final grade
Homework assignments (INL1; 1,5 university credits), (INL2; 1,5 university credits).
Laboratory work (LAB1; 0,7 university credits), (LAB2; 0,8 university credits).
Final oral exam, (TEN1; 3 university credits).
Jens Fransson <firstname.lastname@example.org>
This course for graduate students is given parallel with SG2215 Compressible flow and partly SG2219 Advanced Compressible flow.
Course syllabus valid from: Spring 2010.