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Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory Committee for Aeronautics and publications of other similar research bodies as issued

IT has been found by model tests that the lift of a combination of an aeroplane body and a wing is not in general equal to the sum of the lifts of the two components when tested separately. This difference is broadly referred to as an interference effect. It is dependent on a number of factors which can be generalised into three groups:—

AN interesting feature of modern aeroplane design is the growing use of duct systems. The low drag and heat regeneration obtainable from a cooling duct is now an accomplished fact. Ventilation systems for cabin aircraft have been introduced. In the future we may see duct systems used in connexion with the control of the boundary layer. As aeroplane design is improved, new applications of duct systems continue to appear.

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory Committee for Aeronautics, and publications of other similar research bodies as issued

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory Committee for Aeronautics, and publications of other similar research bodies as issued

The applications of the inverse Wiedemann effect to torque measurements and to torque variation recordings were devised by the writers and the details of the experiments were published in the Reports, Vol. IV, No. 52, and Vol. V, No. 54 (see AIRCRAFT ENGINEERING, Vol. II, July 1930, p. 186. If a ferro‐magnetic bar is furnished with a twisting arm, a force, or variations of a force, can be measured in the same way. The writers constructed a pressure indicator for an internal‐combustion engine and obtained satisfactory results.

Provision must be made on all aeroplanes for the rapid egress of passengers and crew in emergency. Fulfilment of the requirements detailed below will normally be regarded as sufficient, but departures may be permitted or required in particular cases.

In estimating the change of performance of an aircraft resulting from a change in the airscrew‐engine unit—for example, in considering the possible improvement of performance clue to an alteration of gear ratio or to fitting a variable pitch instead of a fixed‐pitch airscrew—the selection of appropriate characteristics and the estimation of the resulting performance is frequently rather troublesome. The absence of airscrew data in a form convenient for immediate application generally makes the computations lengthy.

The third term has been expressed as but in wind tunnel work it is often more convenient to measure were the omission of the dash signifies that the moment is now measured about a wind axis. The two quantities are very closely related and the measurement of one tells us almost as much as if the two were known. The latter, however, tells us either directly or indirectly what effect the addition of fin and rudder will have on the autorotation properties of the wings alone. The damping of fin and rudder being due essentially to the air flow meeting them at an angle on account of the rotation it should theoretically be possible to deduce this dynamic quantity from a simple static test of moment due to yaw angle. An experiment to test this was carried out several years ago but the static test did not give any approximation to the truth. This was ascribed at the time to the shielding of fin and rudder by the tail plane in the rotative experiment and subsequent work has amply confirmed this view. It is now known that shielding by the tail plane is by far the most important factor in determining the efficiency of the vertical surfaces at high angles of attack.

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory Committee for Aeronautics, and publications of other similar research bodies as issued