Author name: Vedant Chaudhari

– 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