- Department of Aerospace Engineering
Course is an extension of the Aerodynamics I class and is a basic theoretical subject in Aerospace Engineering. The class is intended to familiarize students with flow around the wing and the fundamental solution of inviscid and viscous flow cases around aerodynamic profile, and airplane wings at high speed.
- Syllabus of lectures:
1.Model of the flow around the finite span wing, the distribution of induced quantities, Prandtl equation of wing and its solution, Glauert?s solution of the lift distribution along the wing span, aerodynamic characteristics of the wing, Trefftz? plane, Multhopp?s solution of the distribution along the wing span, asymmetric distribution and the influence of nearby objects on the distribution of lift along the wing span, flow separation.
2.Steady one-dimensional adiabatic flow, adiabatic flow with friction and heat exchange.
3.Flow in nozzles and diffusers with variable cross-section. Formation of shock waves, normal shock wave.
4.Two-dimensional potential compressible fluid flow.
5.Flow of viscous compressible fluid.
6.Flow around subsonic aerodynamic profile. Critical Mach number.
7.Subsonic flow and aerodynamic characteristics of straight and swept finite span wings.
8.Two-dimensional supersonic flow. Flow around convex and concave edges.
10.Supersonic aerodynamic characteristics of the wing.
11.Transonic phenomena. Aerodynamic characteristics of the profiles, wings and aircraft in the transonic region. Interaction of boundary layer with an external flow and shock wave. Supercritical profiles. Means for reducing the wave crisis.
13.High speed wind tunnel visit.
- Syllabus of tutorials:
1.Prandtl equation and its solution, Glauert?s method.
2.Derivation and use of equations for compressible flow. Dependence of Mach number and velocity parameter. Expression of dimensionless state variables.
3.Compressibility of gases. Pressure disturbance propagation. Aerodynamic heating.
4.Graphical formulation of the Bernoulli integral and critical values of dimensionless variables.
5.Adiabatic, isoentropic flow in a tube of variable cross-section.
6.Compressible fluid flow through nozzles, diffusers and wind tunnel.
8.Pressure conditions in the high speed measurement probes.
9.Speed ratios at incompressible and compressible flow on the profile.
10.Aerodynamic characteristics of a profile in subsonic compressible flow.
11.Critical Mach number.
12.Supersonic flow around convex and concave shapes.
13.Two-dimensional supersonic flow around an aerodynamic profile. Supersonic profiles.
- Study Objective:
The aim of the course is to deepen the knowledge at the field of aerodynamics by cases of flow around the wing and cases of compressible subsonic, transonic and supersonic flow. Course participants will become familiar with both, the external flow and the flow in channels and nozzles.
- Study materials:
?Barnes W., McCormick, Aerodynamics, Aeronautics and Flight Mechanics, John Wiley & Sons, INC.
?John D.Anderson, Jr., Modern Compressible Flow, McGraw-Hill, INC.
?R.W.Fox, A.T.McDonald, P.J.Pritchard, Introduction to Fluid Mechanics, John Wiley & Sons, INC.
- Further information:
- No time-table has been prepared for this course
- The course is a part of the following study plans: