Author name: Bhagiya Prasad

Constant along a given left-running Mach wave for the internal grid point two” refers to a specific property or parameter that remains constant as a left-running Mach wave propagates through the flow field and interacts with the conditions at the internal grid point labeled as “two.  NOTE: (K+)2 = (K+)3 because K+ is constant along […]

Constant along a given right-running Mach wave refers to a property or parameter that remains the same as the wave propagates through the flow. In other words, it’s a quantity that doesn’t change as the Mach wave moves through the fluid. A “right-running Mach wave” is a specific type of wave associated with changes in

Constant along a given left-running Mach wave refers to a property or parameter that remains the same as the wave propagates through the flow. A “left-running Mach wave” is a specific type of wave associated with changes in the Mach number of the flow. Unlike right-running Mach waves, left-running Mach waves move in the opposite

Constant along a given right-running Mach wave refers to a property or parameter that remains the same as the wave propagates through the flow. In other words, it’s a quantity that doesn’t change as the Mach wave moves through the fluid. A “right-running Mach wave” is a specific type of wave associated with changes in

The wing angle of attack, often denoted as 𝛼, is a fundamental parameter in aerodynamics and aviation. It refers to the angle between the chord line of an airfoil (typically a wing or airfoil section) and the oncoming freestream airflow. The chord line is an imaginary straight line connecting the leading edge and trailing edge

Linearized theory for the wave-drag coefficient is an analytical approach used in aerodynamics to estimate wave drag contributions in supersonic and hypersonic flows. It provides a simplified and linear approximation of the wave-drag coefficient (CD) based on certain assumptions. This linearization is valuable for quick estimations and initial design considerations.  Wave-drag coefficient (cd) Freestream Mach

The wave-drag coefficient (cd) for the supersonic flow over a flat plate is a dimensionless parameter that quantifies the wave drag experienced by the flat plate when it is subjected to a supersonic fluid flow. Wave drag is a significant component of drag in supersonic and hypersonic flows and arises due to the formation of

The lift coefficient (cl) for supersonic flow over a flat plate is a parameter that quantifies the lift or normal force generated by the flat plate when it is subjected to a supersonic fluid flow. This coefficient is specifically used to characterize the lift forces experienced by the flat plate in a supersonic flow regime,

The drag coefficient (cd) for a flat plate with the assumption of a small angle of attack is a parameter that quantifies the drag or resistance to motion experienced by the flat plate when it is subjected to a fluid flow and the angle of attack (𝛼) is relatively small. This assumption is often used

The lift coefficient (cl) for a flat plate with the assumption of a small angle of attack is a parameter that quantifies the lift generated by the flat plate when it is subjected to a fluid flow and the angle of attack (𝛼) is relatively small. This assumption is often used to simplify the analysis