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 Decade: 1940-1949
 Year: 1941
 Collection: National Advisory Committee for Aeronautics Collection
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
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
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
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
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
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
The aerodynamics of a wind-tunnel fan

The aerodynamics of a wind-tunnel fan

Date: January 1, 1941
Creator: Corson, Blake W
Description: The vortex blade-element theory modified to apply to an axial fan working in a duct is reviewed. Thrust and power coefficients for a fan are identified with the corresponding coefficients for airplane propellers. The relation of pressure produced by the fan to the blade-element coefficients is developed. The distribution of axial velocity of fluid through a fan is assumed to be controlled by the fan itself. The radial distribution of tangential velocity imported by the fan to fluid moving through the fan is shown to be independent of the axial-velocity distribution. A nondimensional coefficient, designated the rotation constant, is introduced. This constant is based solely upon design information. The use of the rotation constant in simplifying the design of a fan for a specific operating condition is demonstrated. Based on the use of the rotation constant, a graphical method is outlined by which the performance of a given fan in a given wind tunnel may be predicted and by which the distributions of axial velocity of the fluid through the fan under various operating conditions may be established.
Contributing Partner: UNT Libraries Government Documents Department
Plate method of ground representation for wind-tunnel determination of elevator effectiveness in landing

Plate method of ground representation for wind-tunnel determination of elevator effectiveness in landing

Date: September 1, 1941
Creator: Recant, I G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the effect of vertical position of the wing on the side flow in the region of the vertical tail

Wind-tunnel investigation of the effect of vertical position of the wing on the side flow in the region of the vertical tail

Date: April 1, 1941
Creator: Recant, Isidore G & Wallace, Arthur R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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