Author name: Bhagiya Prasad

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

In aerodynamics, the taper ratio (often represented as “λ” or “TR”) is a geometric parameter used to describe the shape of a wing, specifically a wing’s planform. The taper ratio is defined as the ratio of the tip chord (“ct”) to the root chord (“cr”) of a wing.  “ct” is the tip chord (width) of

The lift coefficient (CL​) for a finite wing is a dimensionless aerodynamic parameter that quantifies the lift generated by the entire wing normalized by the dynamic pressure of the flow and the wing’s reference area. It is a crucial parameter used to characterize the aerodynamic performance and lift generation capability of a finite wing, taking

The lift coefficient (CL​) for a finite wing is a dimensionless aerodynamic parameter that quantifies the lift generated by the entire wing normalized by the dynamic pressure of the flow and the wing’s reference area. It is a crucial parameter used to characterize the aerodynamic performance and lift generation capability of a finite wing, taking

he general circulation distribution along an arbitrary finite wing refers to the distribution of circulation (vorticity) along the span of a wing that is not constrained to any specific idealized shape, such as an elliptic or rectangular wing. The circulation distribution provides insights into how lift is generated and distributed across the span of the

In aerodynamics, “span” refers to the distance between the wingtips of an aircraft or any other lifting surface, such as a wing or a rotor blade. It is a fundamental geometric parameter that characterizes the lateral extent of the lifting surface.  Wing span (b) in m Angle (θ) in rad Span distance (y) in m

The chord length (c(y)) of an airfoil section located at an arbitrary spanwise station y is the straight-line distance between the leading edge and the trailing edge of the airfoil, measured perpendicular to the direction of the airflow. It is a fundamental geometric parameter that characterizes the shape and dimensions of the airfoil section at