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 Collection: Technical Report Archive and Image Library
Theoretical lift and damping in roll at supersonic speeds of thin sweptback tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges

Theoretical lift and damping in roll at supersonic speeds of thin sweptback tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges

Date: January 1, 1950
Creator: Malvestuto, Frank S , Jr; Margolis, Kenneth & Ribner, Herbert S
Description: On the basis of linearized supersonic-flow theory, generalized equations were derived and calculations made for the lift and damping in roll of a limited series of thin sweptback tapered wings. Results are applicable to wings with streamwise tips and for a range of supersonic speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and from the trailing edge of the root section. A further limitation is that the tip Mach lines may not intersect on the wing. For the portion of the wing external to the Mach cones springing from the leading edge of the wing tips, the pressure distributions for lift and roll previously obtained for the triangular wing are valid. For the portion of the wing contained within the wing-tip Mach cones a satisfactory approximation to the exact pressure distribution was obtained by application of a point-source-distribution method developed in NACA-TN-1382. A series of design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweep. (author).
Contributing Partner: UNT Libraries Government Documents Department
Theoretical lift and damping in roll of thin sweptback tapered wings with raked-in and cross-stream wing tips at supersonic speeds.subsonic leading edges

Theoretical lift and damping in roll of thin sweptback tapered wings with raked-in and cross-stream wing tips at supersonic speeds.subsonic leading edges

Date: March 1, 1950
Creator: Margolis, Kenneth
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical lift and damping in roll of thin wings with arbitrary sweep and taper at supersonic speeds : supersonic leading and trailing edges

Theoretical lift and damping in roll of thin wings with arbitrary sweep and taper at supersonic speeds : supersonic leading and trailing edges

Date: May 1, 1950
Creator: Harmon, Sidney M & Jeffreys, Isabella
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical lift and drag of thin triangular wings at supersonic speeds

Theoretical lift and drag of thin triangular wings at supersonic speeds

Date: December 1, 1946
Creator: Brown, Clinton E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical lift and drag of thin triangular wings at supersonic speeds

Theoretical lift and drag of thin triangular wings at supersonic speeds

Date: January 1, 1946
Creator: Brown, Clinton E
Description: A method is derived for calculating the lift and the drag due to lift of point-forward triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary or "supersonic sources" solution of the linearized equation of motion is used to find the potential function of a line of doublets. The flow about the triangular flat plate is then obtained by a surface distribution of these doublet lines. The lift-curve slope of triangular wings is found to be a function of the ratio of the tangent of the apex angle to the tangent of the Mach angle. As the apex angle approaches and becomes greater than the Mach angle, the lift coefficient of the triangular wing becomes equal to that of a two-dimensional supersonic airfoil at the same Mach number. The drag coefficient due to lift of triangular wings with leading edges well behind the Mach cone is shown to be close to that of elliptically loaded wings of the same aspect ratio in subsonic flight. The resultant force on wings with leading edges outside the Mach cone, however, is shown to act normal to the surfaces and thus an induced drag equal to the lift times the ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical lift distribution and upwash velocities for thin wings at supersonic speeds

Theoretical lift distribution and upwash velocities for thin wings at supersonic speeds

Date: November 1, 1947
Creator: Evvard, John C & Turner, L Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical lift due to wing incidence of slender wing-body-tail combinations at zero angle of attack

Theoretical lift due to wing incidence of slender wing-body-tail combinations at zero angle of attack

Date: November 1, 1956
Creator: Sacks, Alvin H
Description: The theoretical lift of a cylindrical afterbody at zero angle of attack due to incidence of the wing is calculated by means of slender-body theory. It is assumed that the vortex sheet becomes fully rolled up ahead of the tail, and the vortex paths in the presence of the body are determined analytically. The total lift of a variety of slender wing-body-tail combinations due to wing incidence is also calculated.
Contributing Partner: UNT Libraries Government Documents Department
The theoretical lift of flat swept-back wings at supersonic speeds

The theoretical lift of flat swept-back wings at supersonic speeds

Date: March 1, 1948
Creator: Cohen, Doris
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical loss relations for low-speed two-dimensional-cascade flow

Theoretical loss relations for low-speed two-dimensional-cascade flow

Date: March 1, 1956
Creator: Lieblein, Seymour & Roudebush, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical maximum performance of liquid fluorine - liquid oxygen mixtures with JP-4 fuel as rocket propellants

Theoretical maximum performance of liquid fluorine - liquid oxygen mixtures with JP-4 fuel as rocket propellants

Date: October 11, 1954
Creator: Gordon, Sanford & Wilkins, Roger L
Description: None
Contributing Partner: UNT Libraries Government Documents Department