Aircraft Design Calculator

The fuel flow rate in the context of aircraft design refers to the rate at which fuel is consumed by the aircraft’s engines to generate the required power for flight   m˙fuel​ is the fuel flow rate, P req​ is the power required by the aircraft, and E fuel​ is the energy content of the […]

The jet thrust equation is a fundamental formula used in aircraft design to describe the thrust produced by a jet engine. F is the thrust produced by the jet engine. m˙ is the mass flow rate of the exhaust gases expelled by the engine. Ve​ is the effective exhaust velocity. V0​ is the velocity of

Power required for level flight is a crucial parameter in aircraft design, representing the amount of power needed to maintain a steady, level flight condition.   Preq​ is the power required for level flight, T is the thrust, V is the velocity of the aircraft, and η is the overall efficiency of the propulsion system.

The Mach angle is a geometric angle that describes the angle between the direction of an object moving through a fluid (like an aircraft) and the Mach cone, which is a shock wave created by the object when it moves through the fluid at a speed greater than the speed of sound. θ is the

The rate of climb is a performance parameter used in aircraft design and aviation to describe the vertical speed at which an aircraft can ascend. It is commonly denoted as ROC and is expressed in feet per minute (ft/min) or meters per second (m/s). T is the thrust generated by the aircraft’s engines, D is

The Static Margin is a measure of the longitudinal stability of an aircraft. It represents the distance between the center of gravity  and the aerodynamic center  normalized by the mean aerodynamic chord SM is the static margin, Xcg​ is the location of the aircraft’s center of gravity, Xac​ is the location of the aerodynamic center,

Potential energy is the energy an object possesses due to its position or state. In the context of aircraft design, potential energy is often associated with the aircraft’s altitude above a reference point, such as the Earth’s surface or a specified datum. PE is the potential energy, m is the mass of the object, g

 Range equation is a fundamental equation in aircraft design that describes the distance an aircraft can travel with a given amount of fuel. The formula for the range (R) of an aircraft is: R is the range, V is the velocity of the aircraft, and D is the drag force acting on the aircraft The

The coefficient of pressure, often denoted as Cp, is a dimensionless quantity used in aerodynamics to describe the distribution of pressure over the surface of an object, such as an aircraft wing The formula for the coefficient of pressure (Cp) is given by:     Cp​ is the coefficient of pressure. p is the local