A strong shock wave during a supersonic flight of a blunt-nosed projectile increases the drag
and aerodynamic heating considerably. A spike can be mounted on the nose of the …

Purpose The purpose of this study is to explore the effects of aerospike and hemispherical
aerodisks on flow characteristics and drag reduction in supersonic flow over a blunt body …

Numerical and experimental studies have been performed at Mach number 2 for
understanding the mechanism of drag reduction by investigating the recirculation region of a …

Effective deduction of air heating load and drag is a critical issue in hypersonic vehicle
engineering applications. In this research, seven various geometrical models have been …

To minimize forebody drag in high-speed flying vehicles such as missiles and rockets,
contemporary research has focused on computational methods to analyze drag reduction …

The inlet is designed to compress the air and increase static pressure. In the present work,
analyses have been carried out using 2D axisymmetric Reynolds averaged Navier Stokes …

Based on emerging technology for shock reconstruction, novel approaches for thermal
protection and drag reduction at supersonic and hypersonic speeds are proposed for study …

In the present study, shock waves produced over different blunt bodies moving at Mach 2.0
at zero angle of attack have been captured and analysed using computational …

The presence of a double aerodisk location changes the shock wave patterns and shock
position. The research shows that the hemispherical spike reduces drag more effectively …