Author name: Bhagiya Prasad

acomp (Compressible Lift Slope for Finite Wing): This parameter represents the rate of change of lift coefficient (Cl) with respect to the angle of attack (α) for a finite wing in compressible flow conditions. It takes into account the effects of compressibility on the wing’s lift behavior. This formula provides a means to estimate the […]

Compressible Lift Slope for Finite Wing represents the rate of change of lift coefficient (Cl) with respect to the angle of attack (α) for a finite wing in compressible flow conditions. It takes into account the effects of compressibility on the wing’s lift behavior.  The equation essentially combines the effects of a0,comp, e₁, and AR

The span efficiency factor e₁ is a measure of how closely the actual lift distribution of a wing resembles an ideal elliptical lift distribution, which would minimize induced drag. 𝜏 provides a way to account for the deviation of the actual lift distribution from the ideal elliptical distribution.  Lift distribution along wing span (𝜏) Span

The lift slope for an infinite wing in a subsonic compressible flow, denoted as “a0,comp,” is a fundamental aerodynamic parameter that characterizes the rate of change of lift coefficient (Cl) with respect to the angle of attack (α) for an infinite wing in subsonic, compressible airflow. The lift slope a0,comp is significant in aerodynamics because

The thickness-to-chord ratio, denoted as “t/c,” is a dimensionless parameter used in aerodynamics and aircraft design to describe the relative thickness of an airfoil or wing section. Specifically, it quantifies the ratio of the maximum thickness (t) of the airfoil to its chord length (c), which is the distance between the leading edge and the

Cp,cr represents the pressure coefficient at a specific point in a compressible flow field where the Mach number reaches its critical value (Mcr). This point often corresponds to a location on an airfoil or an aircraft where flow characteristics change significantly.  Critical pressure coefficient (Cp,cr) Minimum Incompressible Pressure Coefficient (Cp,0)min Critical Mach Number (Mcr)

The minimum pressure coefficient (Cp)​min is a dimensionless parameter used in aerodynamics to describe the lowest value of the pressure coefficient (Cp​) at a specific point on an airfoil or aerodynamic surface. It represents the minimum pressure reached at that point relative to the freestream pressure (p∞​).  Minimum pressure coefficient (Cp)min Incompressible minimum pressure coefficient

Pressure difference, often denoted as Δp, is a measure of the change in pressure between two points in a fluid or gas system. It quantifies the variation in pressure from one location to another and is an essential concept in fluid dynamics, thermodynamics, and engineering.  Critical pressure (pcr) in N/m^2 Freestream pressure (p∞) in N/m^2 Pressure

The critical pressure coefficient with respect to the critical Mach number (Cp,cr​) is a parameter used in aerodynamics to describe the pressure coefficient (Cp​) at which the flow over an airfoil or aerodynamic surface reaches a critical condition associated with the critical Mach number (Mcr​). It provides insights into the behavior of the flow as

The critical pressure coefficient (Cp,cr​) is a specific value of the pressure coefficient (Cp​) at a particular location on an airfoil or aerodynamic surface where the flow reaches a critical condition. This condition is typically associated with the onset of flow separation or the point at which the flow detaches from the surface.  Specific heat