Introductory:
	Airplane Components & control surfaces
	Control volume/control mass systems for analysis
		mass conservation law
		momentum conservation law
	1-D, incompressible flows
		streamlines & streamtubes
	Aerodynamic forces:
		pressure(normal)
		viscous shear (tangential

Compressible, inviscid flows:
	Euler equations

Incompressible, inviscid flows:
	Bernoulli equation
	Continuity equation
	Pitot, static & stagnation pressures

Hydrostatics:
	Hydrostatic equation
	Standard atmosphere
	Manometers;
	Equivalent/true airspeed

Gemetrical parameters
	Airfoil section chord, leading edge, trailing edge, angle of attack
	Wing span
	Wing mean chord

Non-dimensional parameters
	Geometric similarity
	Dynamic similarity
	Lift, drag & moment coefficients
	Reynolds Number
	Aspect ratio
	Mach number
	Angle of attack

Airfoils
	Lift generation: Kutta condition
	Circulation
	Estimation of G
	Kutta-Joukowski Theorem
	Lift-curve slope
	zero-lift angle
	chord
	camber
	thickness
	airfoil lift, drag and moment coefficients
	NACA airfoils
	pressure coefficient
	pressure distributions
	
Wings
	Total wing lift
	
	elliptical lift distribution
	Effect on lift
		trailing vortices, downwash 
		induced angle of attack, effective angle of attack
		momentum equation; determination of downwash & induced 
			angle of attack
		lift-curve slope for a wing
	Induced drag
		Drag polar determined from 3 viewpoints
		
	non-elliptic distributions
		span efficiency factor (Oswald efficiency)
		
Viscous Forces
	No-slip wall condition
	shear stresses at wall
	laminar boundary layer
	    flat plate no pressure gradient
		local skin friction coefficients
		total skin friction
		boundary layer thickness
	    adverse pressure gradient
		boundary layer separation-form drag
	turbulent boundary layer
		transition
		separation delayed relative to laminar separation
		                  
	parasite drag= form  drag + friction drag

Compressible flows
	speed of sound
	integration of Euter equation
	1-D compressible, inviscid relations
	p*, T* etc conditions
	Prandtl-Glauert relation for subsonic airfoils
	pressure coefficient for M=1 on airfoil
	critical Mach number
	Area changes in subsonic, transonic & supersonic flows
	Laval nozzle, supersonic wind tunnel
		stagnation, throat, test section conditions
	Mach lines, Mach angle, shock waves