Aerodynamics and Flight Mechanics (5cr)

Objectives

On successful completion of this module, a student should be able to:⊛ Use the basic principles of fluid mechanics to describe aircraft aerodynamic phenomenon in incompressible and compressible flow regimes.⊛ Understand and analyze the various flows past airfoils, wings as well as nozzles and diffusers which form the basic building blocks of an airplane.⊛ Identify aerodynamic parameters by requirements from mission and flight mechanics.⊛ Perform aircraft performance calculations and identify the critical factors that affect aircraft performance and operations.⊛ Formulate equations of motion for an aircraft in atmospheric flight and motivate the assumptions made to simplify a flight mechanics problem.⊛ Analyze the equilibrium and stability of an aircraft, and explain the basic modes of motion and related mechanisms.Measurable outcomes⊛ Apply flow similarity, non-dimensional coefficients such as the lift and drag coefficient, and non-dimensional parameters such as the Mach number and Reynolds number in aerodynamic modeling of realistic configurations.⊛ Apply mass and momentum conservation equations to aircraft engineering problem.⊛ Explain the relationship between circulation, the generation of lift on an airfoil, and the subsequent loss of lift upon stall.⊛ Explain the motion and deformation of a fluid element using kinematics including the definition of shear strain, normal strain, vorticity, divergence, and the substantial derivative.⊛ Explain the basic elements of the lifting line model for high aspect ratio wings, describe the dependence of lift and induced drag on geometry and performance parameters (e.g. aspect ratio, twist, camber distribution, wing loading, flight speed, etc.) using the lifting line model, and apply the lifting line model to estimate lift, induced drag, and roll moments on high aspect ratio wings.⊛ Explain and apply the thin airfoil theory⊛ Explain the relationship between sound propagation and shock waves , describe the qualitative change in flow conditions (Mach number, pressure, temperature, total pressure, etc.) across shocks and expansion fans (exams), estimate the change in flow conditions across shocks and expansion fans using shock-expansion theory (homework, written exam), explain transonic drag rise including the critical Mach number and the use of wing sweep to delay drag rise.⊛ Use XFOIL to contribute substantially as an individual to a computational aerodynamic project, within a team.⊛ Generate MATLAB scripts to perform flight mechanic calculations & simulations.

Content

Aircraft Aerodynamics⊛ Aerodynamics of airfoils and wings⊛ Brief introduction to high-lift aerodynamics⊛ Short discussions on the aerodynamics of the fuselage, wing-fuselage system and propellers.Aircraft Performance⊛ The international standard atmosphere. True and equivalent airspeed. Straight and level flights. Unpowered flight. Cruise conditions. Motion in a vertical plane. Drag-speed relationships, minimum drag. Lift-to-drag and other non-dimensional ratios.⊛ Gliding flight. Range and endurance for thrust producing engines. Altitude ceiling. Aircraft climb and descent performances. Take-off and landing. Ground-effect.⊛ Combined Flight. Flight envelope limitations. High speed flight. Certification and operational requirements.Flight Dynamics⊛ Coordinate systems, Kinematic and non-linear equations of motion for translation, rotation, attitude and position⊛ Models for the description of external forces and moments, Description of stationary states, Longitudinal motion of the aircraft, Lateral motion of the aircraft, Aerodynamic stability and control derivatives⊛ Linearized equations of motion, Eigenmodes of longitudinal and lateral motionBrief Talks on⊛ Rotary Wing Aerodynamics, Flight Dynamics and Performance - Helicopters and V(S)/TOL⊛ UAV Aerodynamics, Flight Dynamics and Performance⊛ Aerodynamics, Stability & Control at High Angle of Attack

Prerequisites

Code: KONE.700Name: Introduction to Aircraft EngineeringECTS credits: 5Mandatory: Mandatory