Course detail
Aerodynamics II
FSI-OA2 Acad. year: 2018/2019 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
Czech
Number of ECTS credits
4
Supervisor
Department
Learning outcomes of the course unit
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.
Prerequisites
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.
Planned learning activities and teaching methods
The course is taught through lectures explaining the basic principles and theory of the discipline. Exercises are focused on practical topics presented in lectures. Teaching is suplemented by practical laboratory work.
Assesment methods and criteria linked to learning outcomes
Attendance at exercises is obligatory. Attendance at lectures is not obligatory. Awarding a course-unit credit is conditioned with the attendance at exercises, 10 or more of 13, correct elaboration of home works, correct elaboration of report on laboratory measurement and finished problems at home if they were not finished at exercises. Examination is written and oral. In the written part students solve 2 problems during 60 min. The oral part consist of answering 2 questions randomly choosen by a student. Final evaluation is given by the average value of all 4 answers, unless any of them is not a failing mark. In case one of the 4 answers is evaluated as failed, the final result is evaluated as failed.
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.
Specification of controlled education, way of implementation and compensation for absences
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.
The study programmes with the given course
Programme M2I-P: Mechanical Engineering, Master's
branch M-STL: Aircraft Design, 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
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.