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 Collection: National Advisory Committee for Aeronautics Collection
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
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
Flying qualities of a high-performance personal-owner airplane

Flying qualities of a high-performance personal-owner airplane

Date: November 8, 1951
Creator: Adams, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane

Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane

Date: September 12, 1952
Creator: Adams, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Date: March 1, 1956
Creator: Adams, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Date: November 1, 1951
Creator: Adams, Mac C.
Description: By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points. According to linearized theory, the optimum profiles are found to have infinite slope at the nose but zero radius of curvature so that the bodies appear to have pointed noses, a zero slope at the body base, and no variation of wave drag with Mach number. For those bodies having a specified intermediate.diameter (that is, location and magnitude given), the maximum body diameter is shown to be larger, in general, than the specified diameter. It is also shown that, for bodies having a specified maximum diameter, ...
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of the effect of a local change in wing contour on chordwise pressure distribution at high speeds

Flight investigation of the effect of a local change in wing contour on chordwise pressure distribution at high speeds

Date: September 1, 1946
Creator: Adams, Richard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Date: April 11, 1947
Creator: Adams, Richard E.
Description: A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The equipment used to measure the hinge moments of the model proved to be unsatisfactory, and for this reason the hinge-moment data are considered to be only qualitative.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Downwash, Sidewash, and Mach Number Distribution behind a Rectangular Wing at a Mach Number of 2.41

Investigation of Downwash, Sidewash, and Mach Number Distribution behind a Rectangular Wing at a Mach Number of 2.41

Date: September 14, 1950
Creator: Adamson, D.
Description: An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made. In addition the effect of the wing thickness on the sidewash with the wing at 0 angle of attack has been evaluated. Near an angle of attack of 0, agreement between theory and experiment is good, particularly for the downwash results, except in the plane of the wing, inboard of the tip. In this region the proximity of the shed vortex sheet and the departure of the spanwise distribution of vorticity from theory would account for the disagreement. At higher angles of attack prediction of downwash depends on a knowledge of the location of the trailing vortex sheet, in order that the downwash may be corrected for its displacement and distortion. The theoretical location of the trailing ...
Contributing Partner: UNT Libraries Government Documents Department
Investigation of downwash, sidewash, and Mach number distribution behind a rectangular wing at a Mach number of 2.41

Investigation of downwash, sidewash, and Mach number distribution behind a rectangular wing at a Mach number of 2.41

Date: January 1, 1957
Creator: Adamson, David
Description: An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight. In addition, the effect of wing thickness on the sidewash with the wing at 0 degree angle of attack has been evaluated.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of the BMW 801D2 automatic engine control as determined from bench tests

Characteristics of the BMW 801D2 automatic engine control as determined from bench tests

Date: April 1, 1945
Creator: Addie, A N
Description: None
Contributing Partner: UNT Libraries Government Documents Department