Aerospace Engineering - Complete Aerodynamics Guide [2026]

Explore the aerostatics principle and buoyancy that lifts balloons, airships, and hybrid aerostats. Apply Archimedes law to relate lift to displaced fluid, noting balloons lack propulsion and airships have propulsion.

Explore aerodynamic and inertial flying principles, examining lift from Newton's third law, drag tradeoffs with angle of attack, and a survey of fixed-wing and rotorcraft aircraft.

Explore the main airplane components—wing, fuselage, horizontal and vertical surfaces, power plant, landing gear—and how control systems and autopilot automation enable safe flight.

Explore aerodynamic schemes that shape wings, fuselage, and stabilizers to optimize lift, drag, stability, and takeoff performance across biplane and monoplane designs, including flying wing and duck plane concepts.

Explore how body-fixed and velocity-based coordinate systems in aerodynamics determine forces and moments on aircraft, and master angle of attack and sideslip definitions.

Study flight dynamics by examining forces and moments about the aircraft's center of gravity, and how the rudder, elevator, and ailerons control lift, weight, thrust, and drag.

Explore how atmosphere, a mix of nitrogen 78%, oxygen 21%, and argon 0.9%, changes with altitude from troposphere to exosphere, affecting pressure, temperature, and density; standard atmosphere guides aviation data.

Discover how viscosity resists deformation as internal friction, shaping boundary layers and drag. Explore dynamic and kinematic viscosity, Reynolds number, and the laminar-to-turbulent transition that drives aircraft flow.

Learn how air compressibility relates to the speed of sound under isentropic assumptions. It defines Mach number and explains how velocity, temperature, and surface curvature affect compressibility.

Explore the branches of aerodynamics, focusing on external flow and subsonic, transonic, supersonic, and hypersonic regimes, with heat transfer and aircraft examples.

Define transonic flow as regions of subsonic and supersonic air on an aerofoil at Mach numbers roughly 0.2 to 1.3, with altitude shifting speeds of sound and causing shocks.

Examine the physical properties of transonic fluids, including pressure, density, temperature, and viscosity, and how adiabatic and isentropic ideal-gas assumptions influence shock waves and boundary layers under the standard atmosphere.

Explore advanced compressibility by linking bulk modulus to density, define the speed of sound as sqrt(bulk modulus over density), and discuss Mach number effects and subsonic Bernoulli limits.

Discover how the pressure coefficient relates static and dynamic pressure, compare incompressible and compressible flows, and connect cp to Mach number and critical cp for aerodynamics.

Explore Mach waves and shock waves, and how subsonic versus supersonic flow creates Mach wave lines, expansion waves, and oblique or normal shocks in transonic flight.

Explore 2d airfoils as cross sections of unswept wings and analyze stagnation points and circulation. Learn how pressure differences generate lift and pitching moment at angles of attack, transonic effects.

Explore compressibility effects for airfoils by applying the compressibility factor sqrt(1 minus m squared) to the incompressible solution, revealing subsonic and supercritical flow behavior.

Explains how shock waves form on airfoils from expansion and compression waves, and how Mach number, angle of attack, and curvature influence their development.

Explore viscosity in liquids and gases, including temperature effects and pressure independence. Explain how velocity gradients create skin friction and introduce the boundary layer concept by Prando.

Explore boundary layer concepts on airfoils, including displacement and momentum thickness, laminar and turbulent transitions, adverse gradients, separation, and practical wind tunnel testing.

Explore how viscous boundary layers modify airfoil surfaces and the wake, altering pressure, lift, and shock behavior, especially as angle of attack changes and flow separation may occur.

Analyze how laminar versus turbulent boundary layers interact with shock waves to affect lift and drag, and how Mach number and angle of attack drive shock-induced separation.

Explore how wing sweep relates to Mach number and transonic flow, with examples from Concorde, Boeing 767, and Hercules, and compare civil and military design goals.

Explore the key design parameters of swept wings, including span, leading-edge sweep, and trailing-edge sweeps. Examine taper ratio, crank location, fuselage distance, chord, thickness, camber, and angle of attack alpha.

Balance span, sweep, weight, fuel volume, and undercarriage space in wing design. Use aeroelastic considerations and fly-by-wire control for stability and efficient lift-to-drag.

Wing sweep increases cruise speed without extra fuel by reducing the effective Mach number on the wing and increasing the critical Mach number, reducing wave drag. Swept wings keep lift and range with nearly constant L/D and enable a family of aircraft, such as the Airbus A320 family, to fly at the same cruise altitude.

Explore swept wing design factors from the relationship between two-dimensional airfoils and three-dimensional wing parameters, including inviscid to viscous transitions, Reynolds numbers, and CFD versus wind-tunnel testing.

Explore swept wing design fundamentals, including flow development, shock patterns, elliptic loading to reduce induced drag, and winglets and tips to mitigate vorticity on 3D wings.

Explore how swept wings raise critical Mach numbers and maintain lift at high Mach, while reducing drag and enabling higher angles of attack with better lateral stability.

Explore how military swept wings prioritize maneuverability over stability, using fly by wire system to stabilize, and examine how wing sweep, aspect ratio, and Mach number shape shocks and buffet.

Explore airfoil performance by examining lift and drag sources, including wing induced drag and parasitic skin-friction drag, and how Mach, Reynolds, and angle of attack influence lift and drag coefficients.

Analyze transonic airfoil characteristics through the lift curve and drag boundary. Learn how camber, zero angle lift, and Mach effects shape lift, drag, and optimal L over D near peak.

Explore how wave drag arises from compressibility at transonic speeds, as boundary layer changes and shock waves shift lift and drag on wings.

Define the drag divergence Mach number and its relation to the critical Mach number, and estimate wave drag for airfoils and 3D wings with formulas. Explore near-field and far-field methods.

The supercritical airfoil enables steady transonic flight with a large leading-edge radius, flat upper surface, and rear camber to maintain lift and soften the shock.

Learn how the near-field method estimates airfoil drag by measuring surface pressure and skin friction, with CFD enabling detailed boundary layer insights while experimental sensors can disturb flow.

Learn the far-field drag prediction method, which combines viscous drag from wake momentum deficit and wave drag from shock-induced entropy loss, tied to boundary layer displacement on the airfoil.

Estimate drag on an airfoil using the far-field method. Compare viscous and wave drag across Mach conditions and analyze upper and lower surface contributions.

Analyze shock-induced boundary layer separation on an airfoil caused by a strong shock and adverse pressure gradient, and its impact on skin friction and drag, including wave and viscous components.

Explore shock-induced flow separation types, boundary layer reattachment, and separation bubbles as incidence rises, comparing old and new airfoils and adverse pressure gradients.

Apply a boundary-layer based method to estimate 3D wing drag, incorporating trailing and tip vortices, vortex drag, and the roles of circulation and downwash.

Explore lift-dependent and zero-lift drag, along with skin-friction and normal pressure drag methods for wing drag estimation. Utilize wind tunnel data and CFD to measure pressures and infer drag components.

Analyze how swept wing flow separation develops spanwise with increasing incidence and shock strength. Relate pressure coefficients and two-shock patterns to predict and control separation across civil and military wings.

Learn to estimate airfoil performance with Xfoil, loading a NACA 2411, running inviscid and viscous simulations across angles of attack, Mach, and Reynolds numbers, and exporting results.