Author name: Aathif Muzain C

The fuel fraction for the climb phase of a flight, often referred to as “FC” (Fuel for Climb) or “Climb Fuel Fraction,” represents the proportion of an aircraft’s total fuel consumption that is typically consumed during the climb phase of a flight. This fraction is used to estimate the fuel required to ascend from takeoff […]

The fuel fraction for warm-up, taxiing, and take-off, often referred to as “WTT” (Warm-up, Taxi, and Take-off) fuel fraction, is a parameter used in aircraft design and performance analysis. It represents the proportion of an aircraft’s total fuel consumption that is typically consumed during the warm-up, taxiing, and take-off phases of a flight. This fraction

In aircraft design and performance calculations, the “maximum flight speed” (Vmax​) during steady level flight is the highest speed an aircraft can attain while maintaining level flight, where lift equals weight and thrust equals drag. This speed represents a critical parameter for aircraft design and operation. The formula for calculating the maximum flight speed (Vmax​)

The “mean chord” of an aircraft wing is a measure of the average width of the wing from the leading edge to the trailing edge. It is an important parameter in aircraft design and aerodynamics, particularly when calculating lift and drag characteristics. The formula for calculating the mean chord (ˉcˉ) of a wing depends on

Dynamic pressure, denoted as q, is a fundamental parameter in aerodynamics and aircraft design. It represents the kinetic energy per unit volume of a moving fluid (such as air) and is commonly used to describe the dynamic effects of air on an aircraft’s surfaces. Dynamic pressure is crucial in assessing aerodynamic forces and performance. The

Power loading, in the context of aircraft design and performance, is a measure of the aircraft’s engine power in relation to its weight. It indicates how much power is available for each unit of aircraft weight and is an important parameter for assessing an aircraft’s ability to accelerate and climb. The formula for calculating power

The “landing distance” of an aircraft is the distance required for the aircraft to come to a complete stop after touching down on the runway. It includes both the ground roll distance (distance traveled on the runway) and the distance needed to decelerate and stop. Landing distance is a critical parameter for aircraft design and

“Incidence” in the context of aircraft design and aerodynamics refers to the angle at which a wing or other aerodynamic surface is set relative to the aircraft’s fuselage or reference axis. It’s a crucial parameter that affects the wing’s lift and drag characteristics, as well as the overall aerodynamic performance of the aircraft. The formula

The “empty weight” of an aircraft, often referred to as the “basic empty weight” or “unladen weight,” represents the weight of the aircraft without any passengers, cargo, or fuel. It includes the weight of the airframe, engines, avionics, fixed equipment, and any required operating fluids such as oil and hydraulic fluid. The empty weight is

In the context of aircraft design and operations, “disposable load” refers to the total weight of items or cargo that can be carried by an aircraft in addition to its own empty weight (airframe, engines, avionics, etc.) and fuel. This includes passengers, cargo, baggage, and any other items carried on the aircraft for a specific