This is the second part of a paper on aerospace transporters (i.e. fully reusable aeroplane-like piloted launch vehicles) and describes a design concept intended to meet short-term European requirements at minimum development cost. It is generally similar to the European aerospace transporters studied in the 1960s but uses technology developed since then for such projects as Concorde, Spacelab, Ariane and the Space Shuttle.

It is concluded that such a vehicle could be built with more or less existing technology, and, using the costing approach described in the first part of the paper, that the development cost should be less than that of the semi-reusable Hermes/ Ariane 5 combination. A full feasibility study is recommended to check these conclusions.

Experimental and theoretical, small and large amplitude stability data are presented for a pointed and a 0.2 bluntness ratio, 10° semi-angle cone performing pitching oscillations in hypersonic flow at a Mach number of 6.85. Analysis identifies that large amplitude model motion time histories cannot be predicted from a knowledge of small amplitude oscillation stability derivatives data. At the Reynolds numbers of the experiments the pointed and blunted cone are subject to significant hypersonic flow viscous phenomena, which are proposed as the cause of the small to large amplitude stability prediction being invalid.

Reference to the few general papers on aircraft antennas which had been published up to 25 years ago shows that the underlying rules of antenna siting were well understood even though there were few theoretical models at the time. The hardware has changed considerably to reflect new environmental requirements and new manufacturing techniques. In this paper, antenna siting rules are reviewed in the light of aircraft developments and the increasing range of airborne radio systems. Some recent solutions to siting problems are discussed together with some thoughts on possible future problems.

Cylindrical arrays subjected to external flow have been the subject of considerable study in recent years. Much of this study is concerned with a solitary cylinder or cylinder arrays involving many cylinders with the same diameters. Common structures however have cylinders with different diameters. For example, in a reactor, there are small diameter cylinders amongst large ones. In this situation, the dynamic behaviour of the cylinders are different from the cylinder arrays of equal diameters. Since the case of a pair of parallel circular cylinders in a cross-flow constitutes the simplest configuration, its study should be of importance in the understanding of more complicated situations. Various modes of oscillations associated with two interfering cylinders may be found in review papers by Zdravkovich. This note presents some laboratory observations of the response of a rigid twodimensional flexibly mounted smooth circular cylinder, with vibrations restricted to a plane normal to the incident flow, as induced by the vicinity of a rigid parallel circular cylinder of different diameter.