Author name: Bhagiya Prasad

The “drag per unit span” (D′) for a flat plate in supersonic flow refers to the aerodynamic force parallel to the direction of the incoming flow, acting on a unit span length of the flat plate. In the context of a flat plate in supersonic flow, drag is generated due to the pressure difference between […]

The “lift per unit span” (L′) for a flat plate in supersonic flow refers to the aerodynamic force perpendicular to the direction of the incoming flow, acting on a unit span length of the flat plate. In the context of a flat plate in supersonic flow, lift is generated due to the pressure difference between

The “resultant force per unit span,” often denoted as R′, refers to the net aerodynamic force acting on a unit span length of a body, such as an airfoil or wing, in aerodynamics and fluid dynamics. This force takes into account both the lift force and the drag force experienced by the body as it

The “Prandtl-Meyer angle after a deflection,” often denoted as ν2​, refers to the angular deviation of the flow direction after it has been deflected due to interactions with shock waves or other flow disturbances. This concept is widely used in the analysis of compressible fluid dynamics, especially in scenarios involving changes in flow direction.  ν2​

The temperature at downstream in region two, often denoted as T2​, refers to the temperature of the fluid immediately after passing through a compression wave (shock wave). In fluid dynamics, compression waves are characterized by abrupt changes in flow properties, including temperature, pressure, density, and velocity.  Temperature in region two behind the compression wave (T2)

The pressure in region two behind a compression wave, often denoted as p2​, refers to the pressure of the fluid after it has passed through a compression wave (also known as a shock wave). Compression waves are characterized by a sudden increase in pressure, density, and temperature of the fluid. The pressure p2​ is the

The “angle of the rearward Mach line,” often denoted as μ2​, represents the angle formed between the Mach line (a type of shock wave) and the direction of the flow after it has been deflected by a certain angle θ. This concept is commonly encountered in the study of compressible fluid dynamics, especially when analyzing

The “angle of the forward Mach line,” often denoted as μ1​, refers to the angle formed between the Mach line (a type of shock wave) and the direction of the incoming flow in compressible fluid dynamics. This angle is crucial in understanding the behavior of shock waves and their interactions with supersonic flows.  μ1​ is

The Prandtl-Meyer angle after a deflection (ν2​) represents the angular deviation of the flow direction due to a change in the flow’s path caused by shock waves, expansion waves, or other flow disturbances. It quantifies the change in the flow’s direction after passing through these waves.  ν2​ is the Prandtl-Meyer angle after the deflection. ν1​

The deflection angle (θ) is an important concept in compressible fluid dynamics that describes the change in direction of a fluid flow caused by the interaction of shock waves or expansion waves. It’s the difference between the Prandtl-Meyer angles (ν) associated with two different Mach numbers (M). The deflection angle provides insight into how a