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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical investigation of the effects of configuration changes on the center of pressure shift of a body-wing-tail combination due to angle of attack and Mach number at transonic and supersonic speeds

Theoretical investigation of the effects of configuration changes on the center of pressure shift of a body-wing-tail combination due to angle of attack and Mach number at transonic and supersonic speeds

Date: September 2, 1955
Creator: Spahr, J Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the effects of configuration changes on the center-of-pressure shift of a body-wing-tail combination due to angle of attack and mach number at transonic speeds

Theoretical investigation of the effects of configuration changes on the center-of-pressure shift of a body-wing-tail combination due to angle of attack and mach number at transonic speeds

Date: May 1, 1957
Creator: Spahr, J Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Date: December 31, 1952
Creator: Abramovitz, Marvin
Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the effects upon lift of a gap between wing and body of a slender wing-body combination

Theoretical investigation of the effects upon lift of a gap between wing and body of a slender wing-body combination

Date: August 1, 1954
Creator: Dugan, Duane W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the heating-up period of injected fuel droplets vaporizing in air

A theoretical investigation of the heating-up period of injected fuel droplets vaporizing in air

Date: May 1, 1954
Creator: El Wakil, M M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the influence of autopilot natural frequency upon the dynamic performance characteristics of a supersonic canard missile configuration with a pitch-attitude control system

A theoretical investigation of the influence of autopilot natural frequency upon the dynamic performance characteristics of a supersonic canard missile configuration with a pitch-attitude control system

Date: October 9, 1951
Creator: Passera, Anthony L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the influence of auxiliary damping in pitch on the dynamic characteristics of a proportionally controlled supersonic canard missile configuration

A theoretical investigation of the influence of auxiliary damping in pitch on the dynamic characteristics of a proportionally controlled supersonic canard missile configuration

Date: August 25, 1950
Creator: Nelson, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction

A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction

Date: January 1, 1943
Creator: Greenberg, Harry
Description: Charts showing the variation in dynamic stability with the rudder hinge-moment characteristics are presented. A stabilizing rudder floating tendency combined with a high degree of aerodynamic balance is shown to lead to oscillations of increasing amplitude. This dynamic instability is increased by viscous-friction in the rudder control system. The presence of solid friction in the rudder control system will cause steady oscillations of constant amplitude if the floating angle of the rudder per unit angle of sideslip is stabilizing and greater than a certain critical value that depends on other airplane parameters, such as vertical-tail area and airplane moment of inertia about the vertical axis. The amplitude of the steady oscillation is proportional to the amount of friction and is generally quite small but increases as the condition of dynamic instability is approached. An approximate method of calculating the amplitudes of the steady oscillation is explained and is illustrated by a numerical example. A more accurate step-by-step calculation of the motion is also made and it is shown that the agreement with the approximate method is good.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction

A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction

Date: March 1, 1943
Creator: Sternfield, Leonard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the longitudinal response characteristics of a swept-wing fighter airplane having a pitch-attitude control system

Theoretical investigation of the longitudinal response characteristics of a swept-wing fighter airplane having a pitch-attitude control system

Date: January 1, 1953
Creator: Stokes, Fred H
Description: None
Contributing Partner: UNT Libraries Government Documents Department