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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical calculations of the effects of finite sideslip at supersonic speeds on the span loading and rolling moment for families of thin sweptback tapered wings at an angle of attack

Theoretical calculations of the effects of finite sideslip at supersonic speeds on the span loading and rolling moment for families of thin sweptback tapered wings at an angle of attack

Date: November 1, 1953
Creator: Sherman, Windsor L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tips : subsonic leading edges

Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tips : subsonic leading edges

Date: June 1, 1950
Creator: Margolis, Kenneth
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tipssupersonic leading edges

Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tipssupersonic leading edges

Date: July 1, 1950
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical calculations of the lateral stability derivatives for triangular vertical tails with subsonic leading edges traveling at supersonic speeds

Theoretical calculations of the lateral stability derivatives for triangular vertical tails with subsonic leading edges traveling at supersonic speeds

Date: December 1, 1954
Creator: Bobbitt, Percy J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical calculations of the pressure, forces, and moments at supersonic speeds due to various lateral motions acting on thin isolated vertical tails

Theoretical calculations of the pressure, forces, and moments at supersonic speeds due to various lateral motions acting on thin isolated vertical tails

Date: January 1, 1956
Creator: Margolis, Kenneth
Description: Velocity potentials, pressure, distributions, and stability derivatives are derived by use of supersonic linearized theory for families of thin isolated vertical tails performing steady rolling, steady yawing, and constant-lateral-acceleration motions. Vertical-tail families (half-delta and rectangular plan forms) are considered for a broad Mach number range. Also considered are the vertical tail with arbitrary sweepback and taper ratio at Mach numbers for which both the leading edge and trailing edge of the tail are supersonic and the triangular vertical tail with a subsonic leading edge and a supersonic trailing edge. Expressions for potentials, pressures, and stability derivatives are tabulated.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical calculations of the pressures, forces, and moments due to various lateral motions acting on thin isolated vertical tails with supersonic leading and trailing edges

Theoretical calculations of the pressures, forces, and moments due to various lateral motions acting on thin isolated vertical tails with supersonic leading and trailing edges

Date: March 1, 1955
Creator: Margolis, Kenneth
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration

Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration

Date: October 8, 1953
Creator: Margolis, Kenneth
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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
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
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