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 Decade: 1940-1949
 Year: 1941
 Collection: National Advisory Committee for Aeronautics Collection
Design of nozzles for the individual cylinder exhaust jet propulsion system

Design of nozzles for the individual cylinder exhaust jet propulsion system

Date: April 1, 1941
Creator: Voss, Fred
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Date: July 1, 1941
Creator: Greenberg, Harry
Description: The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of span LCAD distributions of swept-back wings

The calculation of span LCAD distributions of swept-back wings

Date: December 1, 1941
Creator: Mutterperl, William
Description: Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
Contributing Partner: UNT Libraries Government Documents Department
Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range

Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range

Date: May 1, 1941
Creator: Donlan, Charles C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Methods of analyzing wind-tunnel data for dynamic flight conditions

Methods of analyzing wind-tunnel data for dynamic flight conditions

Date: October 1, 1941
Creator: Donlan, C J & Recant, I G
Description: The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind-tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral and fin area. Solutions of the lateral equations of motion are given in a form suitable for direct computations. An approximate formula is developed that permits the rapid estimation of the accelerations produced during pull-up maneuvers involving abrupt elevator deflections.
Contributing Partner: UNT Libraries Government Documents Department
Effects of some present-day airplane design trends on requirements for lateral stability

Effects of some present-day airplane design trends on requirements for lateral stability

Date: June 1, 1941
Creator: Bamber, Millard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Supplement to Comparison of automatic control systems

Supplement to Comparison of automatic control systems

Date: August 1, 1941
Creator: Oppelt, W
Description: This analysis deals with the indirect regulator, wherefrom the behavior of the direct regulator is deduced as a limiting case. The prime mover is looked upon as "independent of the load": a change in the adjusting power (to be applied) for the control link (as, for example, in relation to the adjusting path (eta) with pressure valves or the rudder of vessels) does not modify the actions of the prime mover. Mass forces and friction are discounted; "clearance" also is discounted in the transmission links of the regulator.
Contributing Partner: UNT Libraries Government Documents Department
Combined beam-column stresses of aluminum-alloy channel sections

Combined beam-column stresses of aluminum-alloy channel sections

Date: September 1, 1941
Creator: Hutton, J O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A high-speed motion-picture study of normal combustion, knock and preignition in a spark-ignition engines

A high-speed motion-picture study of normal combustion, knock and preignition in a spark-ignition engines

Date: January 1, 1941
Creator: Rothrock, A M
Description: Combustion in a spark-ignition engine was investigated by means of the NACA high-speed motion-picture cameras. This camera is operated at a speed of 40,000 photographs a second and therefore makes possible the study of changes that take place in the intervals as short as 0.000025 second. When the motion pictures are projected at the normal speed of 16 frames a second, any rate of movement shown is slowed down 2500 times. Photographs are presented of normal combustion, of combustion from preignitions, and of knock both with and without preignition. The photographs of combustion show that knock may be preceded by a period of exothermic reaction in the end zone that persists for a time interval of as much as 0.0006 second. The knock takes place in 0.00005 second or less.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of spoiler, deflector, and slot lateral-control devices on wings with full-span split and slotted flaps

Wind-tunnel investigation of spoiler, deflector, and slot lateral-control devices on wings with full-span split and slotted flaps

Date: January 1, 1941
Creator: Wenzinger, Carl J
Description: Report presents the results of an extensive investigation made in the NACA 7 by 10-foot wind tunnel of spoiler, deflector, and slot types of lateral-control device on wings with full-span split and slotted flaps. The static rolling and yawing moments were determined for all the devices tested, and the static hinge moments and the time response were determined for a few devices of each type.
Contributing Partner: UNT Libraries Government Documents Department
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