Aircraft
Engineering

Aircraft performance begins with aerofoil selection and wing design. Lift coefficient, drag polar, and pitching moment characteristics are determined through CFD analysis and validated in wind tunnel testing. Wing sweep, aspect ratio, and taper ratio are traded to optimise cruise efficiency against low-speed handling.

Modern commercial transport wings employ supercritical aerofoils to delay compressibility effects, winglets to reduce induced drag, and natural laminar flow regions where possible. Military aircraft optimise for manoeuvrability and signature management over pure efficiency.

Aircraft structures must carry flight loads with minimum weight while meeting fatigue life requirements over 20,000–90,000 flight cycles. The primary load path — wing spars, fuselage frames, and skin-stringer panels — is sized to limit stresses under ultimate load conditions (1.5× limit load with no failure).

Modern airframes blend aluminium alloys, titanium, and carbon-fibre reinforced polymer (CFRP) composites. The Boeing 787 and Airbus A350 achieve 50%+ composite content by weight, reducing structural mass while improving fatigue resistance compared to metallic equivalents.

Nacelle design, intake aerodynamics, and thrust reverser systems must be integrated without compromising airframe aerodynamics or structural loads. Pylon design carries engine thrust and torque into the wing box while isolating vibration. Engine-out yaw moment sizing drives vertical tail area and rudder authority requirements.