August 2023

Induced drag for steady level flight is a type of drag that arises due to the generation of lift by an aircraft’s wings. When an aircraft is flying in steady level flight, it is producing lift to counteract its weight and maintain a constant altitude. This lift is generated by creating a pressure difference between […]

The lift coefficient (“CL”) for steady level flight is a dimensionless parameter that quantifies the relationship between the lift generated by an aircraft’s wings and the dynamic pressure of the surrounding airflow. In steady level flight, the lift force produced by the wings is equal to the weight of the aircraft, allowing it to maintain

The lift coefficient (“CL”) for steady level flight is a dimensionless parameter that quantifies the relationship between the lift generated by an aircraft’s wings and the dynamic pressure of the surrounding airflow. In steady level flight, the lift force produced by the wings is equal to the weight of the aircraft, allowing it to maintain

Induced drag force, often simply referred to as “induced drag,” is a type of drag that arises due to the generation of lift by an aircraft’s wings. When an aircraft is producing lift, it creates pressure differences between the upper and lower surfaces of the wings. This pressure difference leads to the creation of vortices

The lift curve slope for a finite wing, often denoted as “a,” is an aerodynamic parameter that quantifies the rate of change of lift coefficient (“CL”) with respect to changes in the angle of attack (“α”) for an aircraft wing with finite span. In other words, it represents how much additional lift is generated for

The Oswald efficiency factor, often denoted as “e,” is a dimensionless parameter used in aerodynamics to characterize the efficiency of an aircraft’s wings in generating lift while minimizing drag. It is named after the German aerodynamicist Hans Wolfgang Oswald, who contributed to the understanding of wing efficiency and drag. The Oswald efficiency factor quantifies how

The angle of attack (“α”), often abbreviated as “AOA,” is a fundamental aerodynamic parameter that describes the orientation of an aircraft’s wing or airfoil relative to the oncoming airflow. It is defined as the angle between the chord line of the wing (an imaginary line connecting the leading and trailing edges of the airfoil) and

The lift coefficient (“CL”) is a dimensionless quantity used in aerodynamics to describe the lift generated by an aircraft’s wings or airfoil. It relates the lift force produced by the wings to the dynamic pressure of the airflow and the wing’s geometric characteristics. The lift coefficient is a fundamental parameter that helps aerodynamicists and engineers

The drag coefficients (“CD”) of two wings with different aspect ratios (“AR”) and lift coefficients (“CL”) in the context of aerodynamics. This equation is used to compare the drag of two wings based on their aspect ratios and lift coefficients, taking into account the Oswald efficiency factor (“e”). The below equation represents a way to

A drag polar, also known as a drag coefficient curve, is a graphical representation of the relationship between an aircraft’s lift coefficient (“Cl”) and its drag coefficient (“Cd”) at various angles of attack. It is a fundamental aerodynamic concept that provides valuable information about an aircraft’s performance characteristics and efficiency.  CD is the total drag