THE STANDARDIZATION PROBLEMdoi: 10.1108/eb030720pmid: N/A
A PERENNIALLY thorny subject, which never fails to arouse acute controversy whenever it is broached, is standardization. Some hold the view that all standards are merely clogs on progress; while, at the opposite extreme, there are those who would cut down, for instance, the number of permitted specifications for materials to a tenth, or less, of those that at present exist. The main difficulty is, of course, that, very naturally, any individual will consider that the specifications he is in the habit of using himself are all that is necessary and he feels that others are merely being obstinate in preferring different materials. The number of specifications that have to be available for use entirely, then, depends on the number of individuals—and perhaps their varying degrees of obstinacy.
Slipstream Rotation and StabilityStiesz, W.
doi: 10.1108/eb030721pmid: N/A
SYSTEMATIC experiments carried out by the Dornier‐Werke for several years (for the purpose of investigating flight properties and the quantities of importance for flight performance) included, during 1935, point‐to‐point measurement of the downwash field in front of the tail unit of the Do 17, using twin tube pressure recorders. These flight measurements showed that the stability components of the two halves of the tail plane are not the same on account of the different downwash components produced by rotation of the slipstream. The conclusion that the stability of the aeroplane could be raised by symmetrical arrangement of the airscrews, in accordance with the more favourable starboard side, was well founded, and it was soon recognized that this precaution, in conjunction with the other well‐known advantages of symmetrical direction of rotation of the engine units, is one of the most effective methods for improving the flying properties of two‐ and four‐engined aircraft. This knowledge, which in the meanwhile had been confirmed in various places by wind tunnel tests induced the Dornier‐Werke to generally introduce counterrotating power plants for twin‐engined aircraft.
Prevention of Ice on WindscreensRodert, Lewis A.
doi: 10.1108/eb030723pmid: N/A
THE National Advisory Committee for Aeronautics is conducting a programme of research intended to reduce the risks now attendant on aeroplane operation during icing conditions. A part of this programme is concerned with the prevention of ice on the windshield. The methods investigated involve the use of: (1) heat from an electric source, (2) heat from the engine exhaust, and (3) an alcohol‐dispensing, rotating wiper‐blade. Inasmuch as the problem of ice prevention exists in several forms, it is anticipated that several different methods may find application on the aeroplane. The obstructions of vision through a windshield may result from ice or snow formations on the exterior surface or from the formation of frost on the interior. The object of the present investigation, therefore, was to determine the extent to which the several methods could preserve vision. Observations were also made to determine the capacity of the rotating wiper‐blade to remove rain from the windshield.
Instrument Landing in the U.S.A.doi: 10.1108/eb030724pmid: N/A
THE history of the development of instrument landing extends back a dozen years. In 1928 the National Bureau of Standards began work on a system for the Aeronautics Branch of the Department of Commerce. Using this system, Lt. James H. Doolittle on September 23, 1929, made the first successful instrument landing in history.
Standardization in Aeroplane DesignThompson, John T.
doi: 10.1108/eb030725pmid: N/A
JUDICIOUS standardization applied to aircraft design on a large scale co‐operative basis will form one method by which the mass production of aeroplanes may be expedited. This matter is one which has been recognized with increasing importance for many years by the services and the manufacturers, and it is one which, if handled in the proper manner, will at the same time tend both to improve the science of aircraft design and remove the aeroplane from the experimental status.
The Jigging of Modern Airframesdoi: 10.1108/eb030726pmid: N/A
II—FUSELAGE JIGS (cont.) Girder Fuselages The girder fuselage has, in the last few years, fallen into desuetude, save for some training and light types, yet it has many very decided advantages for rapid production. Perhaps paramount among its virtues is the simplicity of the “plumbing” installations. Chief among the disadvantages is the unsuitability of fabric covering for modern high speeds, yet this can be overcome by careful attention to the method of attachment for the fabric, as may be seen from the success of the Hawker Hurricane and the Morane‐Saulnier MS 406‐C1. In the lower speed ranges the advantages should easily outweigh other considerations, particularly for training aeroplanes where rapid repair on the spot is essential. Again, the success of the de Havilland Tiger Moth, North American Harvard and the Westland Lysander, not to mention the many American light aeroplanes with tubular fuselages speak well in favour of the system.
U.S. Patent Specificationsdoi: 10.1108/eb030727pmid: N/A
In an aeroplane, a control column comprising a grip member, a base member, and a cutaway member provided with slots, said base member being movably mounted in said slots.