Hypersonic Aerodynamics

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the heat transfer rate to a surface in hypersonic flows, which is essential for understanding thermal loads on the surfaces of high-speed vehicles. High-speed flows generate significant heat due to air compression, and this equation helps in managing thermal protection. Symbols: q: […]

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator evaluates the deflection angle for Prandtl-Meyer expansion waves in hypersonic flows. It uses an approximate relation, which becomes more accurate as the Mach numbers (M1 and M2​) increase. The formula helps determine the change in the direction of flow due to expansion, which is

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator approximates the shock wave angle for slender wedges in hypersonic flow. For vehicles with sharp, slender geometries, understanding the shock wave angle is essential for predicting the location of shock waves and their effect on vehicle performance. This relation helps in designing hypersonic

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator evaluates the pressure coefficient for hypersonic flow behind an oblique shock. The pressure coefficient is used to analyze pressure distribution around hypersonic vehicles, influencing drag, lift, and overall aerodynamic performance. Cp​: Pressure coefficient (dimensionless) γ: Ratio of specific heats (dimensionless) M1: Freestream Mach

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator computes the velocity component perpendicular to the flow after a shock in hypersonic conditions. This component is key to predicting flow redirection and determining how shocks interact with the vehicle’s surfaces during high-speed flight. v2​: Velocity component perpendicular to the flow after the

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator evaluates the temperature ratio across a shock wave in hypersonic flow. This ratio is crucial for predicting aerodynamic heating, which affects vehicle design by informing thermal protection systems and heat dissipation strategies in hypersonic flight. T2​: Downstream temperature (K) T1: Upstream (freestream) temperature

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator computes the density ratio across an oblique shock wave in hypersonic conditions. Understanding the density changes in the flow is essential for analyzing aerodynamic forces and predicting shock behaviour on hypersonic bodies. The density ratio helps determine the compression effects of shock waves,

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator determines the ratio of pressures across an oblique shock wave in hypersonic flow. The pressure ratio is a key parameter in analyzing the behavior of supersonic and hypersonic flows encountering oblique shocks, which cause a sudden rise in pressure. It is used in

– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. In boundary layer theory, this equation is crucial for determining the shear stress exerted on a surface submerged in a fluid flow. It plays a pivotal role in calculating skin-friction drag, a significant component of the total aerodynamic drag that a body encounters while moving