Course detail
Aerodynamics II
FSI-OA2-A Acad. year: 2024/2025 Summer semester
Compressibility effects – fundamental laws of compressible fluid flow – kinematics, dynamics of flow field, viscous effects (state equation, conservation of mass – eq. of continuity, Bernoulli’s eq., Euler’s eq., Navier-Stokes eq.). Compressibility effects on airfoil characteristics, wing characteristics and complete aircraft aerodynamic characteristics. Transonic and supersonic flight – selected topics (sound and temperature barrier, area rule, swept wings etc.). Applied aerodynamics computational methods – panel methods – 2D, 3D BEM, theory and applications. FVD and FVM – 1D,2D and 3D, theory and applications. Commercial software, exercise. Aircraft aerodynamic optimization – tools, optimization techniques, multidisciplinary optimization basics.
Language of instruction
English
Number of ECTS credits
5
Supervisor
Department
Entry knowledge
Basic knowledge of mathematics, differentiation and integral calculus, ordinary differential equations ODE and partial differential equations PDE. Basic knowledge of physics and mechanics, statics and dynamics. Basic knowledge of thermomechanics, 1st and 2nd laws of thermomechanics. Basics of fluid flow, equation of continuity, Bernoulli equation. Examination of Aerodynamics I.
Rules for evaluation and completion of the course
Participation at seminars and laboratory exercises is obligatory. Participation at lectures is voluntary. Course-unit credits will be awarded only if: – participation at practical exercises is greater than 11 of 14, – homework assignments are correctly elaborated and submitted, – report of laboratory measurement is submitted, – all problems presented at exercises are correctly finished.. Examination comprises written and possible oral parts. The written one consists of 5 test questions and 2 calculations. Each question per 10 points, each calculation per 20 points. At least 45 points is necessary to pass the exam. Oral part is optional in a case of necessity to clarify some answers from written part.
If attendance at seminars and laboratory exercises is less then 10 of 13 weeks of exercises, a student has to prove he/she elaborated all problems dealt with at missed lessons. If the attendance at exercises is less then 50 % student has to compensate them individualy.
Aims
The aim of the course is to expand knowledge gained at the course Aerodynamics I. Outer flows at subsonic, transonic and supersonic speeds are explained, including inner flows in tubes, nozzles and chanels. Basic knowledge on numerical methods and CFD.
Students will get to know how to solve compressible subsonic and supersonic flows around airfoils, wings and aeroplanes as well as flows in nozzles, chanenls and tubes.
The study programmes with the given course
Programme N-AST-A: Aerospace Technology, Master's, compulsory
Type of course unit
Lecture
26 hours, optionally
Teacher / Lecturer
Syllabus
1. Compressibility effects
1.1 Fundamental laws of compressible fluid flow – fluid kinematics, dynamics, viscosity effects
1.2 Compressibility effects on wing section characteristics
1.3 Compressibility effects on finite wing characteristics
1.4 Compressibility effects on complete aircarft
1.5 Transonic and supersonic flight – selected topics
2. Computational methods in applied aerodynamics
2.1 Panel codes – 2D and 3D BEM, theory and application
2.2 CFD codes – FDM, FVM in 1D, 2D and 3D, theory, application examples, commercial software, exercise
3. Aircraft aerodynamic optimization
3.1 Tools, optimization methods
3.2 Multidisciplinary optimization basics
Laboratory exercise
2 hours, compulsory
Teacher / Lecturer
Syllabus
Outflow of supersonic Laval nozzle.
Exercise
11 hours, compulsory
Teacher / Lecturer
Syllabus
Recalculation of aerodynamic characteristics at subsonic range.
Application of hodpographic transformation.
Comparison of basic methods, accuracy.
Flow at supersonic edges by lineariyed method.
Reflexion of supersonic characteristics at wall and at free boundary.
Mutual interactions of expansion and compression characteristics.
Continuous supersonic expansion at edge of any angle.
Shock waves solution.
Reflexion of shoch wave and continuous expansion.
Solution of flow around an airfoil by CFD, XFOIL.
Solution of flow around an aircraft by CFD, FLUENT.
Evaluation of results, accuracy.