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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical calculations of the supersonic pressure distribution and wave drag for a limited family of tapered sweptback wings with symmetrical parabolic-arc sections at zero lift

Theoretical calculations of the supersonic pressure distribution and wave drag for a limited family of tapered sweptback wings with symmetrical parabolic-arc sections at zero lift

Date: January 1, 1950
Creator: Kainer, Julian H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical characteristics in supersonic flow of constant-chord partial-span control surfaces on rectangular wings having finite thickness

Theoretical characteristics in supersonic flow of constant-chord partial-span control surfaces on rectangular wings having finite thickness

Date: September 1, 1948
Creator: Tucker, Warren A & Nelson, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical characteristics in supersonic flow of two types of control surfaces on triangular wings

Theoretical characteristics in supersonic flow of two types of control surfaces on triangular wings

Date: January 1, 1949
Creator: Tucker, Warren A & Nelson, Robert L
Description: Methods based on the linearized theory for supersonic flow were used to find the characteristics of two types of control surfaces on thin triangular wings. The first type, the constant-chord partial-span flap, was considered to extend either outboard from the center of the wing or inboard from the wing tip. The second type, the full-triangular-tip flap, was treated only for the case in which the Mach number component normal to the leading edge is supersonic. For each type, expressions were found for the lift, rolling-moment, pitching-moment, and hinge-moment characteristics.
Contributing Partner: UNT Libraries Government Documents Department
The theoretical characteristics of triangular-tip control surfaces at supersonic speeds Mach lines behind trailing edges

The theoretical characteristics of triangular-tip control surfaces at supersonic speeds Mach lines behind trailing edges

Date: July 1, 1952
Creator: Kainer, Julian H & King, Mary Dowd
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical characteristics of two-dimensional supersonic control surfaces

Theoretical characteristics of two-dimensional supersonic control surfaces

Date: July 27, 1948
Creator: Morrissette, Robert R & Oborny, Lester F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical characteristics of two-dimensional supersonic control surfaces

Theoretical characteristics of two-dimensional supersonic control surfaces

Date: October 1, 1951
Creator: Morrissette, Robert R & Oborny, Lester F
Description: The "Busemann second-order-approximation theory" for the pressure distribution over a two-dimensional airfoil in supersonic flow was used to determine some of the aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing-edge flaps. The characteristics presented and discussed in this paper are: flap effectiveness factor, rate of change of hinge-moment coefficient with flap deflection, rate of change of the pitching-moment coefficient with flap deflection, rate of change of the pitching-moment coefficient about the mid chord with flap deflection, and the location of the center of pressure of the airfoil-flap combination.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical combustion performance of several high-energy fuels for ramjet engines

Theoretical combustion performance of several high-energy fuels for ramjet engines

Date: January 1, 1958
Creator: Tower, Leonard K; Breitwieser, Roland & Gammon, Benson E
Description: An analytical evaluation of the air and fuel specific-impulse characteristics of magnesium, magnesium octene-1 slurries, aluminum, aluminum octene-1 slurries, boron, boron octene-1 slurries, carbon, hydrogen, alpha-methylnaphthalene, diborane, pentaborane, and octene-1 is presented. While chemical equilibrium was assumed in the combustion process, the expansion was assumed to occur at fixed composition.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical comparison of several methods of thrust augmentation for turbojet engines

Theoretical comparison of several methods of thrust augmentation for turbojet engines

Date: January 1, 1950
Creator: Hall, Eldon W & Wilcox, E Clinton
Description: A theoretical investigation of tail-pipe burning, water injection at the compressor inlet, combination tail-pipe burning plus water injection, bleedoff, and rocket-assist methods thrust augmentation for turbojet engines was made for an engine representative of those in current use. The effect of augmented liquid ratio on augmented thrust ratio and the effects of altitude and flight Mach number on the performance of various methods were determined. The additional take-off weight involved by the use of the different thrust augmentation methods, as well as the effect of the various thrust augmentation methods on the range of a representative aircraft was also investigated.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Comparison of Several Methods of Thrust Augmentation for Turbojet Engines

Theoretical Comparison of Several Methods of Thrust Augmentation for Turbojet Engines

Date: October 27, 1948
Creator: Hall, Eldon W. & Wilcox, E. Clinton
Description: A theoretical investigation has been made of various methods of thrust augmentation for turbojet engines. The method investigated were tail-pipe burning, water injection at the compressor inlet, a combination of tail-pipe burning and water injection, bleedoff in conjunction with water injection at the compressor inlet, and rocket assist. The effect of ratio of augmented-to-normal total liquid consumption, flight conditions, and design compressor pressure ratio on the augmentation produced by each method were determined. A comparison was also made for a given time of operation of the weight of an augmented engine plus fuel and additional liquids to the weight of a standard engine plus fuel producing the same thrust.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical damping in roll and rolling moment due to differential wing incidence for slender cruciform wings and wing-body combinations

Theoretical damping in roll and rolling moment due to differential wing incidence for slender cruciform wings and wing-body combinations

Date: January 1, 1952
Creator: Adams, Gaynor J & DUGAN DUANE W
Description: A method of analysis based on slender-wing theory is developed to investigate the characteristics in roll of slender cruciform wings and wing-body combinations. The method makes use of the conformal mapping processes of classical hydrodynamics which transform the region outside a circle and the region outside an arbitrary arrangement of line segments intersecting at the origin. The method of analysis may be utilized to solve other slender cruciform wing-body problems involving arbitrarily assigned boundary conditions. (author).
Contributing Partner: UNT Libraries Government Documents Department