Experiments are carried out to measure forebody and base heat flux on a typical Crew
Module at Mach numbers 5.8 and 8 over the enthalpy range of 1.5–3.73 MJ/kg. Towards …

A detailed analysis of the mechanisms of the hypersonic laminar near-wake is presented.
Simulations of the compressible Navier-Stokes equations in two dimensions for various …

The objective of this paper is to compute entire flow field over Apollo-II, Aerospace Reentry
Demonstrator (ARD), Orbital Experiment (OREX) with sharp shoulder and rounded shape …

The paper presents aerodynamic coefficients of a blunt-nose re-entry capsule with a conical
cross-section followed by a cone-flare body. A computer code is developed to solve …

The paper evaluates the aerodynamic coefficients on a blunt-nose re-entry capsule with a
conical crosssection followed by a cone-flare body. A computer code is developed to solve …

Re-entry capsules, designed with blunt-body shapes to endure hypersonic air velocities and
heat, encounter instability in the low subsonic regime during the final descent phase …

The main focus of this paper is to compute the flowfield and assess the aerodynamic drag of
Space Recovery Experiment (SRE) modules at freestream Mach 6 at zero angle of …

The determination of aerodynamic characteristics is necessary for designing a re-entry
vehicle. This is an essential input to study the static and dynamic stability of the configuration …

The aerothermodynamic characteristics are necessary for designing an inherently stable
and thermally safe re-entry vehicle. This paper studies the aerothermal characteristics of a …

The article deals with the aerodynamics of atmospheric re-entry of an object idealised as a
flat plate corresponding to the re-entry conditions at hypersonic regime. The rarefied flow …