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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Date: September 1, 1948
Creator: Lindsey, W F; Stevenson, D B & Daley, Bernard N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Date: October 29, 1948
Creator: Davidson, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aileron as an aid to recovery from the spin

The aileron as an aid to recovery from the spin

Date: September 1, 1940
Creator: Neihouse, A I
Description: As part of a general investigation by the NACA of factors that affect the spin, the use of the aileron as an aid to recovery from the spin was studied. Tests of 10 different models, covering a wide range of mass distribution, were made in the NACA free-spinning tunnel to determine the effects of a large downward deflection of the outboard aileron and of normal angular deflections of the ailerons upon recovery characteristics. The results indicate that the direction of aileron setting, with or against the spin, which will aid recovery from the spin depends upon the airplane weight distribution. For monoplanes and for biplanes with lower-wing ailerons, ailerons with the spin will be favorable when the weight is distributed chiefly along the fuselage (single-engine airplanes) and ailerons against the spin will be favorable when the weight is distributed chiefly along the wings (multi engine airplanes). Downward movement of the outboard aileron through a large angle will not always be effective in aiding recovery, the effectiveness of such a movement also being dependent upon the weight distribution of the airplane.
Contributing Partner: UNT Libraries Government Documents Department
Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Date: June 22, 1953
Creator: Drake, Hubert M & Mckay, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Date: July 1, 1955
Creator: Martin, John C & Malvestuto, Frank S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air conditions close to the ground and the effect on airplane landings

Air conditions close to the ground and the effect on airplane landings

Date: January 1, 1935
Creator: Thompson, F L; Peck, W C & Beard, A P
Description: This report presents the results of an investigation undertaken to determine the feasibility of making glide landings in gusty air. Wind velocities were measured at several stations between the ground and a height of 51 feet, and flight tests were made to determine the actual influence of gusts on an airplane gliding close to the ground.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical characteristics of a 45 degree sweptback wing-fuselage combination and the fuselage alone obtained in the Langley 8-foot transonic tunnel

Aeronautical characteristics of a 45 degree sweptback wing-fuselage combination and the fuselage alone obtained in the Langley 8-foot transonic tunnel

Date: September 16, 1952
Creator: Osborne, Robert S & Mugler John P , JR
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Date: April 24, 1947
Creator: Beeler, De E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air flow around finned cylinders

Air flow around finned cylinders

Date: January 1, 1937
Creator: Brevoort, M J & Rollin, Vern G
Description: Report presents the results of a study made to determine the air-flow characteristics around finned cylinders. Air-flow distribution is given for a smooth cylinder, for a finned cylinder having several fin spacings and fin widths, and for a cylinder with several types of baffle with various entrance and exit shapes. The results of these tests show: that flow characteristics around a cylinder are not so critical to changes in fin width as they are to fin spacing; that the entrance of the baffle has a marked influence on its efficiency; that properly designed baffles increase the air flow over the rear of the cylinder; and that these tests check those of heat-transfer tests in the choice of the best baffle.
Contributing Partner: UNT Libraries Government Documents Department
Air flow in the boundary layer of an elliptic cylinder

Air flow in the boundary layer of an elliptic cylinder

Date: January 1, 1939
Creator: Schubauer, G B
Description: The boundary layer of an elliptic cylinder of major and minor axis 11.78 and 3.98 inches, respectively, was investigated in air stream in which the turbulence could be varied. Conditions were arranged so that the flow was two-dimensional with the major axis of the ellipse parallel to the undisturbed stream. Speed distributions across the boundary layer were determined with a hot-wire anemometer at a number of positions about the surface for the lowest and highest intensities of turbulence, with the air speed in both cases sufficiently high to produce a turbulent boundary layer over the downstream part of the surface. The magnitude and the frequency of the speed fluctuations in the boundary layer were also measured by the use of the conventional type of hot-wire turbulence apparatus. Stream turbulence was found to affect both the nature of transition from laminar to turbulent flow in the layer and the position on the surface at which transition occurred. Transition was then investigated in detail with stream turbulence of several different scales and intensities.
Contributing Partner: UNT Libraries Government Documents Department