Aim of the Course:

Aim of the course is deepening knowledge in guided missile aerodynamics. The lectures will cover linear and nonlinear phenomena. Various shapes of wings and configurations are considered. Numerical examples are run to illustrate the typical values of aerodynamic characteristics.

Who should attend?

The course is intended for students, engineers - researchers in the research institutions and engineers in the productions factories. It is advanced course, and it is assumed that attendees of course have good knowledge in general projectile aerodynamics (for basic knowledge see course Classical Aerodynamics of Projectiles and Rockets).


Duration is two weeks (twelve working days); 50 lectures (one lecture duration 45min) , but other arrangement is possible.

Course Outline

1. Review of Guided Weapons
Types of guided weapons and their characteristics, The role of aerodynamics in guided weapon, Configuration layouts, Examples of typical configurations in service, Basic missile characteristics and aerodynamic requirements.
2. Review of Basic Theories in Aerodynamics
Euler equations, Equation of energy and state, Prandtl-Glauert equation, linearized boundary conditions, Pressure coefficient, Navier-Stockes equations, Prandtl equations for boundary layer, Similarity parameters – Mach and Reynolds number.
3. Body Aerodynamics
Body geometry, Slender body theory, Normal force and center of pressure of slender bodies, Non-slender bodies, Influence of shape on normal force and centre of pressure at low and high AOA, Aerodynamic characteristics of body alone at high angle of attack, Cross flow theory.
4. General Wing Aerodynamics in Subsonic, Supersonic and Transonic Speeds
Profile geometry, Wing geometry, Lifting line theory, Prandtl-Glauert rule, Supersonic singularity theory, Lift of infinite straight and swept wing, Lift of small aspect ratio wing.
5. Aerodynamics of Small Aspects Ratio Wings
Results of slender body theory, Vortex theory, Nonlinear cross flow viscous theory, Nonlinear characteristics, Maximal lift and stall angle, Influence of Mach number aspect ratio, taper ratio leading edge sweep angle on nonlinear normal force and centre of pressure.
6. Wing-Body Interference
Slender wing-body theory, interference coefficient, influence of roll angle, Influence of wing geometry on wing-body aerodynamic coefficient, Nonlinear aerodynamic coefficient.
7. Vortex Interference and Wing-Tail Interference
Generation of vortex behind wing section, Lift and vortex intensity by slender body theory and by vortex theory, Downwash – reduction of angle of attack of tail section, calculation of downwash angle by strip theory, nonlinear vortex path and influence of angle of attack.
8. Guided Weapons Control Surfaces
Type of control surfaces – all movable, trailing edge and tip controls, Interference between body and all movable controls, Interference coefficients at zero angle of attack and at angle of attack, Roll due differential deflection of controls, Influence of vortices.
9. Missile Aerodynamic Characteristics
General expression for normal force and centre of pressure of body-wing, body-wing-tail combination, Static derivative with angle of attack and with wing and tail control deflection, Nonlinear coefficient and equivalent angle of attack theory.
10. Drag Prediction
Nose drag – general theory and methods of prediction, Influence of shape - drag of various nose shapes, Friction drag, Boattail drag, Drag of flare and contraction, Base drag, Influence of Mach and Reynolds number, Methods of reduction of base drag, Basis of base bleed, Influence of angle of attack, profile drag, Wing wave drag, Drag due to angle of attack and control deflection.
11. Missile stability and Control Characteristics
General consideration of cruciform missile derivatives, Calculation of damping derivatives, Influence of centre of reduction, Static and dynamic stability, Influence of missile geometry velocity and flight altitude to the derivatives, Control configuration – forward, tail and wing control, Hinge and bending moment.
12. Methods of Calculation of Nonlinear Aerodynamic Coefficients
Review of the method of prediction of aerodynamic coefficients, Panel methods (MISDL, PAN-AIR), Semiempirical method (DATCOM, AP, MISL3, LinPAC), Euler methods (NEARZEUSIN), Navier Stockes methods (Fluent).
13. Numerical Examples by programs WingCoeff and LinPAC
Calculation of normal force coefficient, centre of pressure of wing alone by program WingCoeff and comparison of results from four different sources, and analysis of the influence of geometry and Mach number. Estimation of whole set of aerodynamic derivatives of two sections guided missile at small angle of attack by semiempirical program LinPAC.

Lecturer: Dr Miodrag Curcin