Aircraft Design Calculator

The aspect ratio of the aileron is the ratio of its span to its mean chord. It provides an indication of the aileron’s elongation or how long and slender it is. A higher aspect ratio aileron may generate less drag but could be more susceptible to flutter. Aspect ratio is calculated as: Aileron Span (b_aileron) […]

The Deflection Angle (δ) Of Ailerons on an aircraft is the angle at which these control surfaces are moved to induce a roll motion. The formula for aileron deflection angle is not a single equation but is determined based on aircraft design, control system, and pilot input. Generally, aileron deflection can be represented as: δ

Wing Aspect Ratio (AR) is a fundamental parameter in aircraft design that describes the ratio of a wing’s wingspan to its mean chord (average width). It is an important factor in determining an aircraft’s aerodynamic performance, particularly its lift and induced drag characteristics. Formula: The formula for calculating Wing Aspect Ratio (AR) is straightforward: AR

The effect of wing sweep on the slope of the lift curve, often referred to as the “lift curve slope,” is a critical consideration in aircraft design. The lift curve slope represents how lift changes with changes in angle of attack and is a key factor in determining an aircraft’s aerodynamic performance. Formula: The formula

In aircraft design, “twist” refers to the variation in the angle of incidence or the angle of attack along the span of an aircraft’s wing. Twist is a critical design parameter that can influence an aircraft’s aerodynamic performance, stability, and control. Formula: The formula for calculating twist is not a single equation but rather a

The local speed of sound, denoted as “a_local,” represents the speed at which pressure waves (sound waves) travel through the air at a specific location, altitude, and temperature. It’s a critical parameter in aircraft design and flight operations because it affects various aspects of aerodynamics and aircraft performance. Formula: The formula for calculating the local

True Airspeed (TAS) is an essential parameter in aircraft design and navigation. It represents the actual speed of an aircraft through the surrounding air and is crucial for accurate flight planning and navigation. Formula: The formula for calculating True Airspeed is as follows: TAS is the True Airspeed (in knots or meters per second, depending

Moderate sweep referring to the angle of sweepback (also known as sweep angle), is a design parameter in aircraft engineering that affects the wing’s geometry. Moderate sweep angles are typically between 20 to 40 degrees, where the wing’s leading edge is swept backward from the perpendicular to the aircraft’s longitudinal axis. Formula: The formula for

Structural Weight in aircraft design refers to the total weight of all the structural components and materials used to construct an aircraft, including the fuselage, wings, tail, landing gear, and associated structures. It is a critical parameter that affects an aircraft’s overall weight and performance. Formula: The formula for calculating the structural weight (W_structural) of

Coefficient of Lift Design (Cldesign) typically refers to the maximum coefficient of lift that an aircraft can achieve at a specific configuration. The maximum coefficient of lift (CLmax) is a crucial parameter as it determines the maximum lift an aircraft can generate before it reaches a stall condition. Formula: The maximum coefficient of lift (CLmax)