Author name: Aathif Muzain C

The selection of wing loading based on range (W/S) is an important aspect of aircraft design, particularly when optimizing an aircraft for a specific range performance. Wing loading is the ratio of an aircraft’s weight (W) to its wing’s reference area (S) and is typically expressed in pounds per square foot (psf) or newtons per […]

The flight velocity Vhmax​​ is the maximum horizontal (forward) velocity that an aircraft can achieve in level flight under specific conditions, typically during the cruise phase. It represents the highest speed the aircraft can attain while maintaining a steady level flight without climbing or descending. The formula for calculating Vhmax​​ is as follows: Vhmax​​ is

The drag coefficient (CD​) is a critical parameter in aircraft design and aerodynamics. It quantifies the drag force experienced by an aircraft at a specific flight condition and represents the ratio of the drag force to the dynamic pressure of the air. The formula for calculating the drag coefficient (CD​) is as follows: CD​ is

The lift-dependent drag coefficient (CDi​​) is a component of the total drag coefficient (CD​) and represents the drag that is directly proportional to the lift being generated by the aircraft. It is also known as induced drag and is primarily caused by the production of lift. The formula for calculating the lift-dependent drag coefficient (CDi​​)

The parasite drag coefficient (CD0​​) is a parameter used in aircraft design and aerodynamics to quantify the drag produced by an aircraft when it is in a clean configuration (without flaps or other high-lift devices) and at a specified flight condition (e.g., cruise). It represents the non-lift-dependent drag that opposes the aircraft’s motion through the

The lift coefficient at maximum lift-to-drag ratio (CLmax​​) represents the lift coefficient at which an aircraft achieves its maximum aerodynamic efficiency. This efficiency point is crucial for optimizing an aircraft’s performance, especially during cruising conditions when minimizing drag and maximizing lift are essential for fuel efficiency. The formula for calculating CLmax​​ is as follows: CLmax​​

The drag polar is a graphical representation used in aircraft design and aerodynamics to depict the relationship between an aircraft’s drag coefficient (CD​) and its lift coefficient (CL​) at various flight conditions. It provides valuable insights into an aircraft’s aerodynamic performance, particularly in terms of drag and lift characteristics. The drag polar is typically represented

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