Browsing by Author "Ward, R. E."

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    Aeroplane design study STOL airliner (A71). Part 1- configuration description and data
    (Cranfield Institute of Technology, College of Aeronautics, 1972-06) Howe, D.; Ward, R. E.
    The interest in STOL airliners was reflected in the choice of a 100-118 passenger short range aircraft of this type as the 1971 design project. In addition to the use of the study for detailed investigation by the students of Aircraft Design it also served as the basis for an investigation of the low speed lift and control problems of STOL aircraft. This report is concerned with a description of the configuration adopted and specification of geometric and aerodynamic data. As such it is the first part of the complete reporting of the investigation, subsequent parts being concerned with the more detailed work. The aircraft was designed to operate from 2000 ft long single runways and have a cruising speed of up to 11 - 0.83 at 30,000 ft altitude. The estimated gross weight is 115,000 lb and when landing at 100,000 lb weight the approach speed is 79 knots. The high lift coefficients necessitated by this are obtained either by externally blown jet flaps or an augmenter wing arrangement.
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    Aeroplane design study STOL airliner (A71). Part 3- low speed lift and control
    (Cranfield Institute of Technology, 1972-06) Ward, R. E.
    The potential application of advanced forms of aircraft control to civil operation appears to be capable of being split into two areas. First, those aircraft which are very large, whose rotary inertia tends to reduce the effectiveness of conventional controls. Second, those aircraft whose specification dictates that the aeroplane be flown at very low speed. Again conventional controls become inefficient due to decreased aerodynamic efficiency. The second category of aircraft has been considered in the form of an STOL aircraft. The control problems of an STOL aircraft with a 2000 ft runway capability (Ref.10) have been examined. It has been found that the aircraft is unstable and could require autostabilisation. None of the conventional controls were satisfactory and each required augmentation. The single strip crosswind requirement penalises the design most heavily since this requires over half of the extra control power necessary. The total augmentation for blowing air amounts to an equivalent thrust of approximately 6700 lb. This is equivalent to 11.5 per cent of the total installed aircraft thrust.
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    Design Project 1974/75 A 74 Aircraft Elevator Design.
    (Cranfield University, 1975-05) Mani Abraham, P.; Howe, D.; Tetlow, R.; Ward, R. E.
    Part 1 of this thesis contains the symmetric loading calculations and evolution of the design of elevator for the A 74 Reduced Take off and landing aircraft. Part 2 contains the analysis of final design of elevators. The aircraft is designed to the specifications of DES 7400 and satisfies the British Civil Airworthiness Requirement. A 74 project aircraft has longitudinal control from the tail plane and elevator combination. Tail plane is used for trimming and elevators for pitch controls. All control surfaces are hydraulic power operated. The tailplane uses an inverted supercritical section. The elevator is a four piece arrangement with duplicated hydraulic actuator system. It is of round nose type and the elevator hinge line is at 0.6 C. perpendicular to the aircraft centre line. As elevators are fully power operated mass balancing is not provided. Section 5 in part 1 gives the schemes considered in the design of elevator leading to the final choice of each major part. Section 6 gives the description of final design. Elevator is made of conventional built up construction using Aluminium alloy L 72 sheets and L 65 forgings. Part 2 gives the detailed stress analysis of the final design in accordance with normal aircraft design practise.