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Laboratory experiments with projectiles fired through an ice-fog cloud were used to study the variation of frictional charging with air speed at supersonic speeds. These experiments demonstrated that the charge imparted by each particle decreases with increasing speed at supersonic speeds, apparently because of ice crystal melting on impact. ...These experiments demonstrated that the charge imparted by each particle decreases with increasing speed at supersonic speeds, apparently because of ice crystal melting on impact. Flight instrumentation has been designed and fabricated to measure electrification parameters and effects on a supersonic test aircraft. ...Flight instrumentation has been designed and fabricated to measure electrification parameters and effects on a supersonic test aircraft. The instrumentation measures, charging rate, discharging rate, charge per particle, aircraft potential, streamer current and number of streamer pulses, variation of effective frontal area, and noise spectrum.

This paper describes the results of a study to evaluate parametric variations to a single engine short-takeoff vertical-landing fighter/attack aircraft design. The variables considered involved thrust vectoring, thrust degradation, maximum lift, and other changes to determine the impact on short-takeoff performance, but subject to a vertical-landing capability. The results indicate that there are certain parameters that have a significant effect on short-field performance. Also, the optimal control strategies for transitions from a short-takeoff to forward flight and from forward flight to hover are determined. The results have applicability beyond the configuration evaluated.

The aim of this work is to present the preliminary configuration design studies for an unmanned, lightweight (less than 15 kg), supersonic research aircraft. The studies comprise the aircraft typical mission, the aerodynamic and structural arrangement, preliminary performance, as well as mass distribution. ...It is intended to be the flying test bed for a multicycle engine capable to provide thrust in subsonic, transonic and supersonic regimes. In order to provide validation of the analysis tools, flight performance characteristics of a known, high speed aircraft - North American X-15 - have been also evaluated and compared with the available flight test data. ...And the features associated with the configuration obtained are good indications of the technical feasibility of this supersonic UAV.

The aim of this work is to present the preliminary performance studies of the unmanned, lightweight (less than 10 kg), supersonic research aircraft. The studies comprise the typical mission for the aircraft's first supersonic version, based on the aerodynamic, thrust, and mass characteristics presented in a previous work. ...The studies comprise the typical mission for the aircraft's first supersonic version, based on the aerodynamic, thrust, and mass characteristics presented in a previous work. ...The aircraft, named as “Pohox”, is an Unmanned Air Vehicle, or “UAV”, and is intended to be the flying test bed for a multi cycle engine capable to provide thrust in subsonic, transonic and supersonic regimes. Different tools have been developed to perform the analysis. In the analysis, different flight paths are considered in order to provide insights in terms of fuel consumption, altitude and speed gain.

This paper is a survey of the general requirements for the performance and control of supersonic inlets for turbojet or turbofan propulsion systems for the supersonic transport. The first half of the paper discusses the interaction between inlet and engine performance.

The general problem of applying propulsion systems to supersonic aircraft is discussed briefly and it is shown that neither turbojets nor ramjets are entirely satisfactory when used by themselves. ...A satisfactory solution does result when the powerplants are combined; high supersonic performance then can be achieved without sacrifice of subsonic capability. In order to avoid the confusion resulting from the comparison of propulsion system performance using the special parameters associated with each type of engine, performance is compared along operating altitude-Mach number paths in terms of thrust and specific fuel consumption only.

The Phase III program for development of the U.S. Supersonic Transport was initiated on January 1, 1967. This program includes design and flight qualification of the engine, and 100 hours of flight test in two prototype aircraft. ...A general description is provided of the engine, its performance, and the design features to meet the requirements of the commercial Supersonic Transport. Technology advancements in component design, materials and joining techniques are described as they relate to the development program.

This paper is a review of a Naval Air Systems Command program for exploratory development of a low-cost supersonic turbine engine. Design constraints, performance requirements, estimated engine costs, and latest program results are presented.

The flow field in which the supersonic inlet operates will have important effects on the choice of inlet location, inlet type, and performance.

The basic thinking leading to the selection of the double-delta wing planform as optimum for the United States supersonic transport is outlined in terms of aerodynamic efficiency, propulsive efficiency, weight, sonic boom, and airport noise considerations.

The design of the propulsion control system for the Supersonic Transport (SST) is a culmination of three years of design trade studies. An analysis was made of the throttle systems of the Boeing 747, XB-70, Concorde and other airplanes with a view toward the applicability of these systems for use on the SST.

Since about 99% of the world's operational experience in jet V/STOL is invested in the Harrier, this aircraft is the natural choice of a datum against which new supersonic aircraft designs may be assessed. This paper reviews the key design features of the Harrier aircraft and discusses the operational advantages of vectored thrust that should be considered in the design of supersonic V/STOL fighter aircraft. ...This paper reviews the key design features of the Harrier aircraft and discusses the operational advantages of vectored thrust that should be considered in the design of supersonic V/STOL fighter aircraft. Since these new designs will employ engines with very much higher energy jets, the paper concludes with a description of the V/STOL Ground Effects Facility developed at British Aerospace, Kingston to model test the ground effects caused by these new designs.

This paper presents the results of a study aimed at quantifying the effects of jet source noise reduction, increases in aircraft lift, and reduced aircraft thrust on the take-off noise associated with supersonic civil transports. Supersonic jet noise sources are first described, and their frequency and directivity dependence are defined.

This paper describes recent research in integrated aerodynamic-performance design optimization applied to a supersonic transport wing. The subsonic and supersonic aerodynamics are modeled with linear theory and the aircraft performance is evaluated by using a complete mission analysis.

Three lift/propulsion concepts for a V/STOL supersonic combat aircraft have been compared. The intention was to show the effect of the propulsion system on aircraft weight and size, performance, and life cycle costs for: 1 Vectored thrust with Plenum Chamber Burning (bypass air augmentation) 2 Lift engines and a lift/cruise reheated turbofan 3 A reheated lift/cruise turbofan with a remote augmented lift system (RALS) For a postulated deck-launched intercept mission, the vectored thrust propulsion system with Plenum Chamber Burning gives the smallest and cheapest aircraft having the required performance.

A combination of linear and nonlinear methods was found to be effective in designing a supersonic fighter wing. The design mach number was 1.6, with cruise and maneuver lift coefficients of 0.1 and 0.4.

Integration of propulsion and flight-control systems will provide significant performance improvements for supersonic transport airplanes. Increased engine thrust and reduced fuel consumption can be obtained by controlling engine stall margin as a function of flight and engine operating conditions.

Contemporary Technical opinion is that a second generation Supersonic Transport will need to be commercially viable and meet environmental noise and emissions.

Wind tunnel investigations were conducted on a generic cruciform canard-controlled missile configuration. The model featured fixed or free-rolling tail-fin afterbodies to provide an expanded aerodynamic data base with particular emphasis on alleviating large induced rolling moments and/or for providing canard roll control throughout the entire test angle-of-attack range. The tests were conducted in the NASA Langley Unitary Plan Wind Tunnel at Mach numbers from 2.50 to 3.50 at a constant Reynolds number per foot of 2.00 × 106. Selected test results are presented to show the effects of a fixed or free-rolling tail-fin afterbody on the static longitudinal and lateral-directional aerodynamic characteristics of a canard-controlled missile with pitch, yaw, and roll control at model roll angles of 0° and 45°.

This document specifies the requirements for the design objectives for handling qualities applicable to transport aircraft operating in the subsonic, transonic, and supersonic speed range. These objectives are not necessarily applicable to rotor or VTOL aircraft.