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Stability derivatives at supersonic speeds of thin rectangular wings with diagonals ahead of tip Mach lines

Description: The investigation includes steady and accelerated vertical and longitudinal motions and steady rolling, yawing, sideslipping, and pitching for Mach numbers and aspect ratios greater than those for which the Mach line from the leading edge of the tip section intersects the trailing edge of the opposite tip section. The stability derivatives are derived with respect to principal body axes and then transformed to a system of stability axes. Theoretical results are obtained, by means of the linearized theory, for the surface-velocity-potential functions, surface-pressure distributions, and stability derivatives for various motions at supersonic speeds of thin flat rectangular wings without dihedral.
Date: June 30, 1948
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Determination of the damping moment in yawing for tapered wings with partial-span flaps

Description: Report presenting a method for determining the damping moment in yawing for tapered wings with partial-span flaps. Charts are given for untwisted wings with various taper ratios, aspect ratios, and center-span flaps. Theoretical and experimental results are provided.
Date: August 1943
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Additional design charts relating to the stalling of tapered wings

Description: From Introduction: "The present report, therefore, may be considered a supplement to reference 1. The combined scope of the stall charts of reference 1, designated A, and of the present work, designated B, is summarized in the following table: For the wing with root thickness ratio to 18 was also investigated.
Date: January 1943
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails

Description: Report presenting an analysis to compare longitudinal stability and control characteristics obtained with a conventional fixed-stabilizer, an adjustable-stabilizer, and an all-movable horizontal tail. The tail-area requirements, control forces required in the critical landing condition, static margin, control-force gradients in a dive recovery, and elevator-free stability are investigated.
Date: October 1945
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Stability derivatives of thin rectangular wings at supersonic speeds: Wing diagonals ahead of tip mach lines

Description: Report presenting theoretical results for the surface-velocity-potential functions, surface-pressure distributions, and stability derivatives for various motions at supersonic speeds of thin flat rectangular wings without dihedral. The investigation included steady and accelerating vertical and longitudinal motions and steady rolling, yawing, sideslipping, and pitching for Mach numbers are provided.
Date: November 1948
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

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

Description: Report presenting a theoretical investigation of the supersonic wave drag at zero lift of a series of untapered sweptback wings with thin symmetrical biconvex parabolic-arc sections. The investigation was extended to include Mach numbers which bring the Mach line behind the wing leading edge and also to include wings of rectangular plan form.
Date: October 1947
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Determination of the Effect of Wing Flexibility on Lateral Maneuverability and a Comparison of Calculated Rolling Effectiveness With Flight Results

Description: Report presenting an analysis which shows that, when account is taken of sideslip and wing flexibility, the calculated rolling maneuverability of an airplane is in good agreement with the results obtained from flight tests. The method used avoids the complications of successive approximations but is nevertheless believed to be more nearly accurate than other methods based on semirigid-wing assumptions. The method is applied to a wing of tubular shell construction and the procedure is illustrated for a modern pursuit airplane.
Date: January 1944
Creator: Harmon, Sidney M.
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

Description: Report presenting theoretical results for the lateral force and yawing moment due to combined angle of attack and roll. The thin wings are tapered and have leading and trailing edges which are each swept at a constant angle; the tips are parallel to the center section.
Date: July 1950
Creator: Harmon, Sidney M. & Martin, John C.
Partner: UNT Libraries Government Documents Department

Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio: Wings Swept Behind the Mach Lines

Description: "On the basis of a recently developed theory for finite sweptback wings at supersonic speeds, calculations of the supersonic wave drag at zero lift were made for a series of wings having thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios. The results are presented in a unified form so that a single chart permits the direct determination of the wave drag for this family of airfoils for an extensive range of aspect ratio and sweepback angle for stream Mach numbers up to a value corresponding to that at which the Mach line coincides with the wing leading edge. The calculations showed that in general the wave-drag coefficient decreased with increasing sweepback" (p. 1).
Date: February 21, 1947
Creator: Harmon, Sidney M. & Swanson, Margaret D.
Partner: UNT Libraries Government Documents Department

Calculations of the supersonic wave drag of nonlifting wings with arbitrary sweepback and aspect ratio : wings swept behind the Mach lines

Description: Report presenting calculations of the supersonic wave drag at zero lift for a series of wings with thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios.
Date: May 1947
Creator: Harmon, Sidney M. & Swanson, Margaret D.
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

Description: Report presenting generalized expressions obtained by means of the linearized theory for the surface velocity potentials and the surface-pressure distributions due to lift and roll, the lift-curve slope, and the damping-in-roll derivative for a series of thin wings. The results of the investigation are presented in the form of generalized design curves for rapid estimation of the derivatives.
Date: May 1950
Creator: Harmon, Sidney M. & Jeffreys, Isabella
Partner: UNT Libraries Government Documents Department