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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical supersonic characteristics of inboard trailing-edge flaps having arbitrary sweep and taper : Mach lines behind flap leading and trailing edges

Theoretical supersonic characteristics of inboard trailing-edge flaps having arbitrary sweep and taper : Mach lines behind flap leading and trailing edges

Date: October 1, 1950
Creator: Kainer, Julian H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical supersonic force and moment coefficients on a sideslipping vertical- and horizontal-tail combination with subsonic leading edges and supersonic trailing edges

Theoretical supersonic force and moment coefficients on a sideslipping vertical- and horizontal-tail combination with subsonic leading edges and supersonic trailing edges

Date: March 1, 1954
Creator: Malvestuto, Frank S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical supersonic lift and drag characteristics of symmetrical wedge-shape-airfoil sections as affected by sweepback outside the Mach cone

Theoretical supersonic lift and drag characteristics of symmetrical wedge-shape-airfoil sections as affected by sweepback outside the Mach cone

Date: March 1, 1947
Creator: Ivey, H Reese
Description: The theoretical supersonic section lift and drag characteristics of thin wedge-shape, untapered airfoils with sweepback are presented. The results apply to those parts of the wing in two dimensional flow and are not applicable to wings swept back within the Mach cone of the center section. The results may also be applied to swept-forward wings if the angle of sweep is not enough to put the wing within the Mach cone from the tips.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical supersonic wave drag of untapered sweptback and rectangular wings at zero lift

Theoretical supersonic wave drag of untapered sweptback and rectangular wings at zero lift

Date: October 1, 1947
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical symmetric span loading at subsonic speeds for wings having arbitrary plan form

Theoretical symmetric span loading at subsonic speeds for wings having arbitrary plan form

Date: January 1, 1948
Creator: Deyoung, John
Description: A method is shown by which the symmetric span loading for a certain class of wings can be simply found. The geometry of these wings is limited only to the extent that they must have symmetry about the root chord, must have a straight quarter-chord line over the semispan, and must have no discontinuities in twist. A procedure is shown for finding the lift-curve slope, pitching moment, center of lift, and induced drag from the span load distribution. A method of accounting for the effects of Mach number and for changes in section lift-curve slope is also given. Charts are presented which give directly the characteristics of many wings. Other charts are presented which reduce the problem of finding the symmetric loading on all wings falling within the prescribed limits to the solution of not more than four simultaneous equations. The loadings and wing characteristics predicted by the theory are compared to those given by other theories and by experiment. It is concluded that the results given by the subject theory are satisfactory. The theory is applied to a number of wings to exhibit the effects of such variables as sweep, aspect ratio, taper, and twist. The results are compared ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical symmetric span loading due to flap deflection for wings of arbitrary plan form at subsonic speeds

Theoretical symmetric span loading due to flap deflection for wings of arbitrary plan form at subsonic speeds

Date: January 1, 1952
Creator: Deyoung, John
Description: A simplified lifting-surface theory is applied to the problem of evaluating span loading due to flap deflection for arbitrary wing plan forms. With the resulting procedure, the effects of flap deflection on the span loading and associated aerodynamic characteristics can be easily computed for any wing which is symmetrical about the root chord and which has a straight quarter-chord line over the wing semispan. The effects of compressibility and spanwise variation of section lift-curve slope are taken into account by the procedure. The method presented can also be used to calculate the downwash in the vertical center of the wake of a wing which has arbitrary spanwise loading.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical turbojet thrust augmentation by evaporation of water during compression as determined by use of a Mollier diagram

Theoretical turbojet thrust augmentation by evaporation of water during compression as determined by use of a Mollier diagram

Date: June 1, 1950
Creator: Trout, Arthur M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical wave drag and lift of thin supersonic ring airfoils

Theoretical wave drag and lift of thin supersonic ring airfoils

Date: August 1, 1948
Creator: Mirels, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical wave drag of shrouded airfoils and bodies

Theoretical wave drag of shrouded airfoils and bodies

Date: June 1, 1956
Creator: Byrd, Paul F
Description: Formulas for the wave drag of shrouded symmetrical airfoils and shrouded bodies of revolution of arbitrary shape are derived by means of linearized theory. In the case of the airfoils, the shroud consists of flat plates and for the bodies of revolution the shroud is a cylindrical shell. The results obtained hold for a Mach number range dependent on the geometry of the configuration. Expressions are also given for determining a class of body shapes for which the wave drag is theoretically zero.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical wave drags and pressure distributions for axially symmetric open-nose bodies

Theoretical wave drags and pressure distributions for axially symmetric open-nose bodies

Date: June 1, 1950
Creator: Jack, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department