A 16-section interactive reference guide covering the core disciplines of aerospace engineering. Includes aerodynamic lift and drag theory, airfoil and wing design, the International Standard Atmosphere, compressible flow and Mach number, aircraft propulsion (propellers, turbojets, turbofans) and rocket propulsion (the Tsiolkovsky rocket equation), orbital mechanics and Kepler's laws, aircraft stability and control, aerospace structures and materials, airframe fatigue and damage tolerance, avionics systems, aircraft certification, UAV/drone design, and flight performance formulas.
All the foundational areas of aerospace engineering are covered: Aerodynamics & Flight Sciences (the lift equation, angle of attack and stall, induced and parasite drag, the drag polar, airfoil geometry and NACA series, aspect ratio and sweep, compressible flow, Mach number, isentropic relations, normal and oblique shock waves, and the standard atmosphere model); Propulsion & Astrodynamics (the Brayton cycle, turbojet/turbofan/turboprop tradeoffs, bypass ratio and TSFC, the rocket thrust equation, specific impulse, the Tsiolkovsky rocket equation, staging, Kepler's laws, the vis-viva equation, Hohmann transfers, and escape velocity); and Vehicle Engineering (static and dynamic stability, the three flight axes, load factor and semimonocoque structure, spars/ribs/stringers, aluminum/titanium/composite materials, fatigue S-N behavior and the Paris law, avionics and CNS systems, FAR Part 23 vs Part 25 certification, and UAV/drone design fundamentals).
Use the Prev / Next buttons at the bottom, or press the arrow keys on your keyboard. Click the ☰ menu button in the top-right corner to open the table of contents and jump directly to any of the 16 sections. The progress bar at the top tracks your position through all sections. Scroll the mouse wheel to advance or go back.
The sections build on each other: aerodynamics (lift, drag, airfoils) sets up compressible flow and propulsion, which together explain how aircraft and rockets generate and use thrust. Orbital mechanics extends those same energy and momentum principles into space. Stability and control, structures and materials, and fatigue then cover how the vehicle is shaped, built, and kept safe over its service life, while avionics, certification, and UAV design round out the systems and regulatory context every practicing aerospace engineer works within.
All formulas use standard aerospace convention with SI or mixed units as commonly published (for example, specific impulse in seconds, Mach number as a dimensionless ratio). Before applying any formula, check which flow regime you are in — incompressible aerodynamics below about Mach 0.3, compressible isentropic relations up to shock formation, and shock relations beyond it — since using the wrong regime's equations is the single most common analysis error. For structures, always distinguish limit load (no permanent deformation) from ultimate load (no failure, with safety factor applied).
The lift equation is L = ½ρV²SC_L, where ρ is air density, V is airspeed, S is wing area, and C_L is the lift coefficient set by angle of attack. Because V is squared, doubling airspeed quadruples lift — which is why small airspeed changes near stall speed matter so much for takeoff and landing safety.
The Tsiolkovsky rocket equation, Δv = Isp·g₀·ln(m₀/m_f), relates the velocity change a rocket can achieve to its exhaust velocity (via specific impulse) and its mass ratio. Because the relationship is logarithmic, reaching orbital velocity (~9.4 km/s of delta-v) requires an exponentially large propellant fraction. Staging — discarding empty tanks and engines during ascent — removes dead weight the equation would otherwise penalize, which is why virtually every orbital rocket is built in multiple stages.
ISA defines a sea-level standard day (15°C, 101,325 Pa, 1.225 kg/m³) and a fixed temperature lapse rate of −6.5°C per kilometer through the troposphere up to the tropopause at about 11 km. Pressure and density fall roughly exponentially with altitude because each layer of air supports the weight of everything above it. ISA gives engineers and pilots a common reference so aircraft performance, engine ratings, and altimeters can all be compared on equal terms, with real conditions expressed as deviations like ISA +15.
Induced drag is the unavoidable byproduct of generating lift, arising from wingtip vortices — it is inversely proportional to airspeed squared and dominates at low speed and high angle of attack. Parasite drag (skin friction, form, and interference drag) comes from simply pushing the aircraft through the air and grows with the square of airspeed, dominating at high speed. Total drag is minimized at the speed where the two are equal.
In subsonic flow, a converging duct accelerates gas, but at Mach 1 the relationship between area and Mach number reverses: supersonic flow accelerates only in a diverging duct. This is why a converging-diverging (de Laval) nozzle is required to reach supersonic exhaust speeds — the flow reaches Mach 1 at the throat, where it is choked, and then keeps accelerating through the diverging section, a principle used in both rocket nozzles and supersonic wind tunnels.
Disclaimer: This reference guide summarizes publicly available aerospace engineering principles and standards for educational purposes only. Always consult the official adopted edition of the applicable regulation or standard (FAR, CS, NASA, AIAA, ASME, etc.) for design, certification, and compliance decisions.