Author name: Bhagiya Prasad

The Linearized Supersonic Pressure Coefficient, often denoted as Cp​, is a term used in aerodynamics to describe the pressure distribution around an object moving at supersonic speeds. It provides a measure of how the local pressure at a specific point on the object’s surface deviates from the freestream pressure.  Pressure coefficient (Cp) Angle (θ) in […]

Horizontal perturbation velocity (u^) is a term used in aerodynamics to describe the component of the velocity perturbation that is oriented horizontally, perpendicular to the direction of the freestream flow. It represents the change in horizontal velocity caused by aerodynamic disturbances or perturbations in the flow around an object, such as an aircraft wing.  Horizontal

Vertical perturbation velocity (v^) is a term used in aerodynamics to describe the component of the velocity perturbation that is oriented vertically, perpendicular to the direction of the freestream flow. It represents the change in vertical velocity caused by aerodynamic disturbances or perturbations in the flow around an object, such as an aircraft wing.   NOTE:

Horizontal perturbation velocity (u^) is a term used in aerodynamics to describe the component of the velocity perturbation that is oriented horizontally, perpendicular to the direction of the freestream flow. It represents the change in horizontal velocity caused by aerodynamic disturbances or perturbations in the flow around an object, such as an aircraft wing.   Horizontal

The Prandtl-Glauert factor (λ) is a mathematical factor used in aerodynamics to account for compressibility effects when an object is moving at speeds close to the speed of sound (in the transonic regime). It is primarily used in subsonic and transonic aerodynamic calculations to approximate the effects of compressibility.  Prandtl-Glauert factor (𝜆) Freestream Mach number

The Prandtl-Glauert factor (λ), often denoted as the Mach correction factor, is a mathematical factor used in aerodynamics to account for the compressibility effects that occur when an object, such as an aircraft, moves at speeds close to the speed of sound. This factor is used primarily in subsonic and transonic aerodynamic calculations to approximate

The lift slope for an infinite swept wing in compressible flow, denoted as a0,comp​, is a key aerodynamic parameter that describes the rate of change of lift coefficient (CL​) with respect to the angle of attack (α) for an infinitely long swept wing operating in compressible flow conditions. This parameter quantifies how the lift generated

The component of the freestream Mach number for a swept wing, denoted as M∞,n​, represents the portion of the freestream Mach number (M∞​) that is normal or perpendicular to the wing’s leading edge or the wing reference line. It is a vector component of the freestream Mach number that acts in the direction perpendicular to

The lift slope for an infinite swept wing in compressible flow, denoted as a0,comp​, is a parameter used in aerodynamics to describe the rate of change of lift coefficient (CL​) with respect to angle of attack (α) for an infinitely long swept wing operating in compressible flow conditions. It quantifies how the lift generated by

The lift slope for low aspect ratio straight wings in compressible flow, often denoted as acomp​, is a parameter that characterizes the rate of change of the lift coefficient (CL​) with respect to the angle of attack (α) under compressible flow conditions. It quantifies how the lift generated by the wing changes as the angle