Pressure and heat flux measurements at the surface of an asymmetric cone at Mach number 4.6 in ISL’s shock tunnel STB

Abstract

New concepts for guiding and controlling the flight of projectiles in the hypersonic speed regime up to Mach number 10 or more, such as the missile's outer contour deformation are under investigation for future applications. Strong lateral forces can be obtained if the deformation takes place at the projectile's nose. For this purpose a flat ramp with ramp angles between 15 deg and 18 deg was machined on conical nose models of 20 deg half angle to create a cone asymmetry. With these models differential interferometry flow visualisations, surface pressure and heat transfer measurements were performed at Mach number 4.6 and 7 km altitude atmospheric conditions at the ISL's shock tunnel STB to examine the resulting flow around the asymmetric cone model.