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Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Description: Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date: June 17, 1954
Creator: Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Transonic wind-tunnel investigation of static longitudinal force and moment characteristics of two wing-body combinations with clipped-tip and full delta wings of aspect ratio 1.73

Description: Report presenting an investigation in the transonic blowdown tunnel to obtain static longitudinal force and moment characteristics of two wings, one with an aspect ratio of 1.73 and 3-percent-thick delta wing and one with an aspect-ratio-1.73 4-percent-thick clipped delta wing mounted on a slender body. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: September 14, 1956
Creator: Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Experimental investigation of an NACA 64A010 airfoil section with 41 suction slots on each surface for control of laminar boundary layer

Description: Report presenting an investigation of boundary-layer suction through flush surface slots as a means for increasing the extent of laminar flow on the NACA 64A010 airfoil section. Results regarding slot modifications, suction distribution, and drag results are provided.
Date: April 1952
Creator: Burrows, Dale L. & Schwartzberg, Milton A.
Partner: UNT Libraries Government Documents Department

A transonic wind-tunnel investigation of the longitudinal force and moment characteristics of a plane and a cambered 3-percent-thick delta wing of aspect ratio 3 on a slender body

Description: Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.
Date: November 15, 1954
Creator: Burrows, Dale L. & Palmer, William E.
Partner: UNT Libraries Government Documents Department

Investigations relating to the extension of laminar flow by means of boundary-layer suction through slots

Description: Report presenting an experimental investigation of boundary-layer suction through slots as a means of increasing the extent of laminar flow on airfoil sections. Results regarding slot geometry and arrangement, suction slots in an unfavorable pressure gradients, suction slots in a favorable pressure gradient, and a determination of the relations controlling the distribution of suction slots are provided.
Date: October 1949
Creator: Loftin, Laurence K., Jr. & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of a model of a wingless fin-controlled missile to obtain static stability and control characteristics through a range of Mach numbers from 0.5 to 0.88

Description: From Summary: "An investigation at medium to high subsonic speeds has been conducted in the Langley low-turbulence pressure tunnel to determine the static stability and control characteristics and to measure the fin normal forces and moments for a model of a wingless fin-controlled missile. With the horizontal-fin deflection limited to a maximum of 6 degrees, longitudinally stable and trimmed flight could not be maintained beyond an angle of attack of 17 degrees for a Mach number of 0.88 and beyond 20 degrees for a Mach number of 0.50 for any center-of-gravity location without the use of some auxiliary stability or control device such as jet vanes."
Date: April 12, 1954
Creator: Burrows, Dale L. & Newman, Ernest E.
Partner: UNT Libraries Government Documents Department

Investigations Relating to the Extension of Laminar Flow by Means of Boundary-Layer Suction Through Slots

Description: Note presenting experimental investigations of boundary-layer suction through slots as a means of increasing the extent of laminar flow on airfoil sections. The results show that, with the use of suitable slots, substantial increases in the extent of laminar flow can be achieved by boundary-layer control with only a small expenditure of power. Results regarding slot geometry and arrangement, suction slots in an unfavorable pressure gradient, suction slots in a favorable pressure gradient, and determinations of the relations controlling the distribution of suction slots are provided.
Date: October 1949
Creator: Loftin, Laurence K., Jr. & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of an NACA 64A010 Airfoil Section With 41 Suction Slots on Each Surface for Control of Laminar Boundary Layer

Description: Note presenting an investigation of boundary-layer suction through flush surface slots as a means for increasing the extent of laminar flow on the NACA 64A010 airfoil section. This is desirable because the advantages resulting from the attainment of extensive laminar flow over an aerodynamic surface are well-known. Results regarding the extent of the flow, slot modifications, suction distribution, and drag results are provided.
Date: April 1952
Creator: Burrows, Dale L. & Schwartzberg, Milton A.
Partner: UNT Libraries Government Documents Department

Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. The surface of the airfoil that was tested had a lot of waves and irregularities, but the theoretically predicted stabilizing effect of area suction on a smooth flat plate was still observed.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Experimental and theoretical studies of area suction for the control of the laminar boundary layer on an NACA 64A010 airfoil

Description: From Summary: "A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of suction to produce continuous inflow through the surface of the airfoil (area suction). In addition to the experimental investigation, a related theoretical analysis was made to provide a basis of comparison for the test results."
Date: March 30, 1951
Creator: Braslow, Albert L.; Burrows, Dale L.; Tetervin, Neal & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil

Description: Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Experimental and Theoretical Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil

Description: Note presenting a low-turbulence wind tunnel investigation of an NACA 64A010 airfoil with a porous surface of sintered bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by use of suction to produce continuous inflow through the surface of the model. Results regarding the uncompartmented model, compartmented model, observations on stability of laminar boundary layer, and theoretical calculations are provided.
Date: July 1949
Creator: Burrows, Dale L.; Braslow, Albert L. & Terervin, Neal
Partner: UNT Libraries Government Documents Department