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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical investigation of longitudinal response characteristics of a swept-wing fighter airplane having a normal acceleration control system and a comparison with other types of systems

Theoretical investigation of longitudinal response characteristics of a swept-wing fighter airplane having a normal acceleration control system and a comparison with other types of systems

Date: July 1, 1954
Creator: Stokes, Fred H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Theoretical Investigation of Longitudinal Stability of Airplane with Free Controls Including Effect of Friction in Control System

A Theoretical Investigation of Longitudinal Stability of Airplane with Free Controls Including Effect of Friction in Control System

Date: January 1, 1944
Creator: Greenberg, Harry
Description: The relation between the elevator hinge-moment parameters and the control-forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of longitudinal stability of airplanes with free controls including effect of friction in control system

A theoretical investigation of longitudinal stability of airplanes with free controls including effect of friction in control system

Date: February 1, 1944
Creator: Sternfield, Leonard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Theoretical Investigation of Longitudinal Stability of Airplanes with Free Controls Including Effect of Friction in Control System

A Theoretical Investigation of Longitudinal Stability of Airplanes with Free Controls Including Effect of Friction in Control System

Date: January 1, 1944
Creator: Greenberg, Harry & Sternfield, Leonard
Description: The relation between the elevator hinge moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance. The stability of the short period oscillations is shown as a series of boundaries giving the limits of the stable regions in terms of the elevator hinge moment parameters. The effects of static stability, elevator moment of inertia, elevator mass unbalance, and airplane density are also considered. Dynamic instability is likely to occur if there is mass unbalance of the elevator control system combined with a small restoring tendency (high aerodynamic balance). This instability can be prevented by a rearrangement of the unbalancing weights which, however, involves an increase of the amount of weight necessary. It can also be prevented by the addition of viscous friction to the elevator control system provided the airplane center of gravity is not behind a certain critical position. For high values of the density parameter, which correspond to high altitudes of flight, the addition of moderate amounts of viscous friction may be destabilizing even when the airplane is statically stable. In this case, increasing the viscous friction makes the oscillation stable again. ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of methods for computing drag from wake surveys at high subsonic speeds

Theoretical investigation of methods for computing drag from wake surveys at high subsonic speeds

Date: June 1, 1945
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of Submerged Inlets at Low Speeds

Theoretical Investigation of Submerged Inlets at Low Speeds

Date: August 1, 1951
Creator: Sacks, Alvin H.
Description: The general characteristics of the flow field in a submerged air inlet are investigated by theoretical, wind-tunnel, and visual-flow studies. Equations are developed for calculating the laminar and turbulent boundary-layer growth along the ramp floor for parallel, divergent, and convergent ramp walls, and a general equation is derived relating the boundary-layer pressure losses to the boundary-layer thickness. It is demonstrated that the growth of the boundary layer on the floor of the divergent-ramp inlet is retarded and that a vortex pair is generated in such an inlet. Functional relationships are established between the pressure losses in the vortices and the geometry of the inlet. A general discussion of the boundary layer and vortex formations is included, in which variations of the various losses and of the incremental external drag with mass-flow ratio are considered. Effects of compressibility are also discussed.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of subsonic oscillatory blade-row aerodynamics

Theoretical investigation of subsonic oscillatory blade-row aerodynamics

Date: February 1, 1958
Creator: Lane, Frank
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the aerodynamics of wing-tail combinations performing time-dependent motions at supersonic speeds

A theoretical investigation of the aerodynamics of wing-tail combinations performing time-dependent motions at supersonic speeds

Date: May 1, 1954
Creator: Martin, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the attack phase of an automatic interceptor system at supersonic speeds with particular attention to aerodynamic and dynamic representation of the interceptor

Theoretical investigation of the attack phase of an automatic interceptor system at supersonic speeds with particular attention to aerodynamic and dynamic representation of the interceptor

Date: January 25, 1957
Creator: Sherman, Windsor L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Theoretical Investigation of the Drag of Generalized Aircraft Configurations in Supersonic Flow

A Theoretical Investigation of the Drag of Generalized Aircraft Configurations in Supersonic Flow

Date: January 1, 1957
Creator: Graham, E. W.
Description: It seems possible that, in supersonic flight, unconventional arrangements of wings and bodies may offer advantages in the form of drag reduction. It is the purpose of this report to consider the methods for determining the pressure drag for such unconventional configurations, and to consider a few of the possibilities for drag reduction in highly idealized aircraft. The idealized aircraft are defined by distributions of lift and volume in three-dimensional space, and Hayes' method of drag evaluation, which is well adapted to such problems, is the fundamental tool employed. Other methods of drag evaluation are considered also wherever they appear to offer amplifications. The basic singularities such as sources, dipoles, lifting elements and volume elements are discussed, and some of the useful inter-relations between these elements are presented. Hayes' method of drag evaluation is derived in detail starting with the general momentum theorem. In going from planar systems to spatial systems certain new problems arise. For example, interference between lift and thickness distributions generally appears, and such effects are used to explain the difference between the non-zero wave drag of Sears-Haack bodies and the zero wave drag of Ferrari's ring wing plus central body. Another new feature of the spatial ...
Contributing Partner: UNT Libraries Government Documents Department