An experimental investigation has been performed into the effects of leading edge bluntness and sweep on the mean flow characteristics of a glancing shock wave turbulent boundary layer interaction. A series of blunt ...

Using the design requirements of Remotely Piloted Vehicles (RPV's), selected for wind tunnel testing over the Reynolds number range 3 x 105 to 1 x 106. The first aerofoil, NACA 643-418, showed a degradation ...

The present study analyses the effects of a number of geometric parameters on the performance of a trailing edge control flap on a hypersonic body. The tests were conducted in a gun tunnel at Mach 8.2 and Mach 12.3. The ...

An experimental study has been performed at M∞=8.2 and Re∞/cm=93000 to examine: 1. The effect of strakes on the aerodynamic characteristics and performance on slender elliptic cone missile configurations. Some information ...

This thesis is divided into, two distinct parts. Part I describes the design and development of an intermittent cryogenic wind-tunnel, in which the cold conditions are generated by the expansion of high pressure gas. The ...

The effects of leading edge bluntness and sweep angle on the three dimensional glancing shock wave - boundary layer interaction have been investigated. A large number of hemi-cylindrically blunted fins with leading edge ...