This paper provides an overview of the activities associated with the aerodynamic database which is being developed in support of NASA’s Hyper-X scramjet flight experiments. Three flight tests are planned as part of the Hyper-X program. Each will utilize a small, nonrecoverable research vehicle with an airframe integrated scramjet propulsion engine. The research vehicles will be individually ro...

A mathematical model is developed for an anti-tank missile and its guidance algorithms. The aerodynamic model is separated into two parts, the airframe and external lifting surfaces in order to model damage to the airframe. Radar data is compared to that of the proposed model and it is shown that the model accurately replicates the true flight dynamics. Two types of field handling damage are mo...

An advanced, modular paneling scheme has been developed for atmospheric flight vehicles with an aim of predicting the drag during hypersonic flight. A generic, three-dimensional grid generation algorithm has been developed for this effort that allows the construction of detailed aircraft geometries using the concept of geometric overlap in three-dimensional spaces. The use of Bernstein polynomi...

The airframe-integrated linear-spike nozzle concept applied to an external nozzle for high-speed aircraft was evaluated with regard to the thrust augmentation capability and the trim balance. The main focus was on the vehicle aftbody. The baseline airframe geometry was first premised to be a hypersonic waverider design. The baseline aftbody case had an external nozzle comprised of a simple dive...

It is envisaged that the next generation of civil aero-engines will employ high bypass ratios to lower specific thrust and improve propulsive efficiency. This trend likely be accompanied with integration compact nacelle exhausts in podded under-wing installation positions are close coupled airframe. leads requirement for a comprehensive methodology able predict aerodynamic performance combined ...

The open hole tensile and compressive strengths are important design parameters in qualifying fiber reinforced laminates for a wide variety of structural applications in the aerospace industry. In this paper, we present a unified model that can be used for predicting both these strengths (tensile and compressive) using the same set of coupon level, material property data. As a prelude to the un...