Aircraft Design Calculator

In aircraft design and aerodynamics, “load factor” refers to the ratio of the aerodynamic forces acting on an aircraft to the aircraft’s weight. It is a measure of the aircraft’s acceleration in response to these forces, and it is expressed as a dimensionless number or in units of gravitational acceleration (g), which is approximately 9.81 […]

In aircraft design, the term “range” refers to the maximum distance an aircraft can travel on a single tank of fuel or a single battery charge in the case of electric aircraft. It is a critical performance parameter because it determines how far an aircraft can fly without needing to refuel or recharge, which is

Wing loading (WL) is a fundamental aerodynamic parameter used in aviation to describe the distribution of an aircraft’s weight over its wing’s surface area. It is typically expressed in units of force per unit area, such as pounds per square foot (lb/ft²) in the Imperial system or newtons per square meter (N/m²) in the International

The aircraft weight equation, in simple terms, calculates the total mass or weight of an aircraft. The weight of an aircraft is a critical parameter in aviation because it affects various aspects of aircraft performance, such as lift, thrust, and fuel consumption. The equation for aircraft weight is as follows:     Weight (W) is

The aspect ratio of an aircraft’s wing has a significant impact on its aerodynamic performance. Higher aspect ratios generally result in lower induced drag (drag generated by the lift produced), which can lead to improved fuel efficiency and better glide characteristics. However, very high aspect ratios can also make an aircraft less maneuverable. In aircraft

The thrust equation relates the thrust produced by a propulsion system to the mass flow rate of the exhaust gases and their velocity. In SI (International System of Units) units, the thrust equation is typically expressed as       F is the thrust in Newtons (N). m (pronounced “m-dot”) is the mass flow rate of

The lift equation is fundamental in aerodynamics and is used to calculate the lift force required to keep an object, like an aircraft, in the air based on its design, the surrounding air density, the reference area, and its velocity relative to the air. Lift Force (L) is measured in Newtons (N). Coefficient of Lift

A force must be created that equals or exceeds the force of gravity. This force is called lift. L is the Overall Lift in N Lw is Wing Lift in N Ltis Tail Lift in N