The object of this report is to present the results of a theoretical and experimental study of the effect, on the performance of air speed indicators, of the different atmospheric conditions experienced at various altitudes.
Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, expenditures, problems, recommendations and a compilation of technical reports produced.
Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, expenditures, and problems.
Report includes specifications for the use and production of instruments used in the navigation and operation of aircraft. Specifications are included for the following instruments: barometer or altimeter, compass, air speed meter, inclinometer, drift meter, tachometer, oil gauge, oil pressure gauge, gasoline gauge, gasoline flow indicator, distance indicator, barograph, angle of attack indicator, radiator temperature indicator, gasoline feed system pressure indicator, sextant, airplane director.
Report describes the principles of operation and characteristics of some of the instruments which have been devised or used to measure both low and high speeds of aeroplanes. Since the pitot tube is the instrument which has been most commonly used in the United States and Great Britain as a speedometer for aeroplanes, it is treated first and somewhat more fully than the others.
Report presents the experimental results of fabrics used for balloons and aeroplanes. Tensile properties, surface roughness, skin friction, flammability, permeability, and water absorption were tested for different combinations of materials.
A report to the Weather Bureau, Washington DC, from the chairman of the Subcommittee on the Atmosphere in Relation to Aeronautics describing the activities accomplished and the proposal of work to be undertaken by the subcommittee.
Part 1 presents the results of a wind tunnel test of a biplane model with an 18 inch span. The lift, drift, and pitching moment were measured for a series of angles of incidence corresponding to the maximum possible changes of flight attitude. Only the discussion of symmetrical or longitudinal changes is given. From the observed rate of variation of the forces and pitching moment, it was possible to calculate the derivatives needed in the complete theory of longitudinal stability in still air. The damping of the pitching oscillation was also determined experimentally. Part 2 presents a theoretical method for determining the effects of gusts on aeroplanes in the following cases: (1) head-on gusts rising from 0 to j feet per second with various degrees of sharpness, (2) up gusts of the same type, (3) rotary gusts of the same type, (4) rear gusts and down gusts are included by merely changing the sign of j.
Report presents results that show that it is possible to furnish efficient terminal connections that would allow for repairs for aviation wires and cables and eliminate the use of acid solder and blow torch.
Report presents requirements of internal combustion engines suitable for aircraft. Topics include: (1) service requirements for aeronautic engines - power versus weight, reliability, and adaptability factors, (2) general characteristics of present aero engines, (3) aero engine processes and functions of parts versus power-weight ratio, reliability, and adaptability factors, and (4) general arrangement, form, proportions, and materials of aero parts - power-weight ratio, reliability, and adaptability.