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In order for the supersonic transport to be economically feasible, the cost of the fuel should be essentially equivalent to ASTM type A and type A-1 prices. ...The results of the survey indicated that some of the commercial aviation kerosene fuel being supplied to the commercial subsonic jets of today may be satisfactory for use in the supersonic transport.

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.

General technical requirements are presented which led to the selection of titanium alloys as the basic structural material for a Mach 2.7 supersonic transport. Discussion includes important material properties such as strength, toughness, corrosion and stress corrosion resistance, metallurgical stability, and fatigue.

This paper discusses the design considerations for supersonic transport aircraft of four types-one with a variable sweep wing and three with fixed wings.

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.

Hydrocarbon fuels capable of meeting high performance standards in advanced supersonic propulsion systems can be produced in substantial volume at reasonable cost from petroleum streams by hydrogenating aromatic concentrates or processing certain cuts from selected crudes.

A concept of cooling passenger and crew compartments for the supersonic transport utilizes air flowing outwardly through the wall insulation to prevent aerodynamic heat from passing through the wall.

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

The effects of aircraft-loading parameters on the fatigue behavior of titanium alloy have been investigated for a schedule of stresses representing the flight-by-flight variation of stress at a point in the lower wing surface of a supersonic airplane. The effects on fatigue life of design mean stress, minimum stress for ground-air-ground cycles, taxi stress, thermal stress, elevated temperature, salt corrosion, and flight duration were investigated.

Supersonic capable STOVL fighter/attack aircraft can provide capabilities for close support and air superiority which will be highly desirable in the future.

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.

An impingement of axisymmetric supersonic jet on the ground is simulated numerically to evaluate the jet flow configuration on the ground, which inclines from 0 to 45 degrees, with a real gas assumption for two-dimensional simulations and with an ideal gas assumption for three-dimensional simulations. ...An experimental study of the underexpanded axisymmetric supersonic N2 jets impinging on a ground which inclines from 0 to 45 degrees is also discussed.

A numerical simulation of shock wave generation by high-pressure and high-speed spray jet has been conducted to compare to the experimental results obtained by X-ray radiographic technique. Using the space-time conservation element solution element (CESE) method and the stochastic particle techniques to account for fuel injections and droplet collisions, supersonic-spray-induced shock waves are successfully simulated. Similar to the experimental condition, a non-evaporating diesel spray in a chamber filled with inert gas sulfur hexafluoride (SF6) at 1 atm pressure under room temperature (30° C) is simulated. To simulate the needle lift effect in the single-hole diesel injector, various injection-rate profiles were employed. In addition, the effects of discharge coefficients, with Cd ranging from 0.8 to 1.0, were also considered to simulate the shock generation processes in the leading spray front.

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.