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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical investigation at subsonic speeds of the flow ahead of a slender inclined parabolic-arc body of revolution and correlation with experimental data obtained at low speeds

Theoretical investigation at subsonic speeds of the flow ahead of a slender inclined parabolic-arc body of revolution and correlation with experimental data obtained at low speeds

Date: July 1, 1954
Creator: Letko, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation based on experimental frequency-response measurements of an automatic altitude control in combination with supersonic missile configuration

Theoretical investigation based on experimental frequency-response measurements of an automatic altitude control in combination with supersonic missile configuration

Date: August 3, 1954
Creator: Seaberg, Ernest C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot

Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot

Date: October 19, 1950
Creator: Seaberg, Ernest C.
Description: The proportional-plus-flicker automatic pilot operates by a nonlinear principle whereby a fast-acting flicker servomotor response is combined with a low-speed proportional servomotor response for the purpose of obtaining supersonic stability and control. Essentially, the autopilot maintains a zero reference about which the output is proportional to the input. However, a flicker response overrides this proportional response at a fixed angle of gimbal displacement on either side of the zero gyroscope reference. Therefore, in contrast to other high speed control systems, the design requirements are simplified because the two components of the proportional-flicker control system are easy to build separately and they can be combined in a relatively simple manner. By application of the proportional-flicker principle, satisfactory stability can be obtained by the proper adjustment of the variable factors in the autopilot mechanism; namely, the proportional gain, the amplitude of flicker control deflection, the autopilot time-lag factor (the time-lag between flicker and proportional operation), and the point in the range that the autopilot switches from a flicker to a proportional system. There is a possibility that these factors can be adjusted so that a more rapid response time (the time to reach steady state) is obtained with the non-linear proportional-flicker autopilot ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of a proportional-plus-flicker automatic pilot

Theoretical investigation of a proportional-plus-flicker automatic pilot

Date: May 1, 1955
Creator: Seaberg, Ernest C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of an automatic control system with primary sensitivity to normal accelerations as used to control a supersonic canard missile configuration

Theoretical investigation of an automatic control system with primary sensitivity to normal accelerations as used to control a supersonic canard missile configuration

Date: July 10, 1951
Creator: Seaberg, Ernest C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of drag reduction in maintaining the laminar boundary layer by suction

Theoretical investigation of drag reduction in maintaining the laminar boundary layer by suction

Date: June 1, 1947
Creator: Ulrich, A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of flutter of two-dimensional flat panels with one surface exposed to supersonic potential flow

Theoretical investigation of flutter of two-dimensional flat panels with one surface exposed to supersonic potential flow

Date: January 1, 1956
Creator: Nelson, Herbert C
Description: A Rayleigh type analysis involving chosen modes of the panel as degrees of freedom is used to treat the flutter of a two-dimensional flat panel supported at its leading and trailing edges and subjected to a middle-plane tensile force. The panel has a supersonic stream passing over its upper surface and still air below. The aerodynamic forces due to the supersonic stream are obtained from the theory for linearized two-dimensional unsteady flow and the forces due to the still air are obtained from acoustical theory. In order to study the effect of increasing the number of modes in the analysis, two and then four modes are employed. The modes used are the first four natural modes of the panel in a vacuum with no tensile force acting. The analysis includes these variables: Mach number, structural damping, tensile force, density of the still air, and edge fixity (clamped and pinned). For certain combinations of these variables, stability boundaries are obtained which can be used to determine the panel thickness required to prevent flutter for any panel material and altitude.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of hydrodynamic impact loads on scalloped-bottom seaplanes and comparisons with experiment

A theoretical investigation of hydrodynamic impact loads on scalloped-bottom seaplanes and comparisons with experiment

Date: January 1, 1947
Creator: Milwitzky, Benjamin
Description: An analytical method is presented for calculating the hydrodynamic impact loads and motions experienced by seaplane floats and hulls with scalloped (fluted) bottoms. The analysis treats vertical impact at zero trim in addition to the more general problem of the step impact of a seaplane at positive trim where the flight path is oblique to the keel and to the water surface. Also considered are the transformations required to represent impacts into waves.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of hydrodynamic impact loads on scalloped-bottom seaplanes and comparisons with experiment

A theoretical investigation of hydrodynamic impact loads on scalloped-bottom seaplanes and comparisons with experiment

Date: July 1, 1947
Creator: Milwitzky, Benjamin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of laminar heat transfer on yawed infinite cylinders in supersonic flow and a comparison with experimental data

Theoretical investigation of laminar heat transfer on yawed infinite cylinders in supersonic flow and a comparison with experimental data

Date: August 9, 1955
Creator: Beckwith, Ivan E
Description: None
Contributing Partner: UNT Libraries Government Documents Department