Aircraft Design Calculator

The root chord of an exposed wing, often denoted as croot​, is the chord length of the wing at its innermost section, typically where the wing attaches to the fuselage. It is one of the key geometric parameters of the wing and plays a crucial role in determining the aircraft’s aerodynamic characteristics. The formula for […]

The local chord (c) of an aircraft’s wing is the length of a straight line segment from the leading edge to the trailing edge of the wing at a specific point along the wing’s span. It is a critical parameter in aerodynamics and aircraft design because it determines the wing’s geometry and influences various aerodynamic

Aerodynamic balance, often denoted as AB, is a parameter used in aircraft design to assess the balance between aerodynamic forces acting on an aircraft’s control surfaces and the moments created by those forces around the aircraft’s center of gravity (CG). It helps designers ensure that control surfaces are correctly sized and positioned for stable and

Cruise Speed for Maximum Endurance (Vmax endurance​) is the airspeed at which an aircraft can achieve its maximum endurance, which is the ability to remain in the air for the longest possible time while consuming the least amount of fuel. This is an important parameter in aircraft design, especially for missions that require extended loitering or

The landing distance of an aircraft is the distance it requires to decelerate, descend, and touch down safely on a runway or landing surface during a landing maneuver. It is an essential parameter in aircraft design and operation, as it determines the runway length needed for a safe landing. The formula for calculating landing distance

The takeoff distance of an aircraft is the distance it requires to accelerate from a standstill on the runway to a specified speed and become airborne. It is a critical parameter in aircraft design and operation, as it determines the runway length needed for a safe takeoff. The formula for calculating takeoff distance (STO​) is

Specific Excess Power (Psp​) is a parameter used in aircraft performance analysis. It measures the excess power available to an aircraft on a per-unit-mass basis. Specifically, it represents the difference between the engine’s thrust (T) and the power required to maintain a certain flight condition. The formula for calculating Specific Excess Power (Psp​) is as

The thrust-to-weight ratio (T/W) is a critical parameter in aircraft design and performance analysis. It represents the ratio of an aircraft’s engine thrust (T) to its total weight (W). This ratio provides valuable information about an aircraft’s ability to accelerate, climb, and perform various flight maneuvers. The formula for calculating thrust-to-weight ratio is straightforward: T/W

The drag polar is a graphical representation of an aircraft’s drag characteristics at various angles of attack and airspeeds. It typically consists of a curve that shows how the aircraft’s drag coefficient (CD​) changes with changes in angle of attack (α) or airspeed. The formula for the drag coefficient (CD​) itself is not a simple

The term “(L/D)max” refers to the maximum lift-to-drag ratio that an aircraft can achieve. It is a crucial parameter in aircraft design and performance analysis because it indicates the point at which the aircraft is operating most efficiently in terms of generating lift for a given amount of drag. Pilots and engineers use this ratio