National Advisory Committee for Aeronautics (NACA) - 369 Matching Results

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NACA: University Conference on Aerodynamics, A Compilation of the Papers Presented

Description: This document contains reproductions of the technical papers presented at the NACA - University Conference on Aerodynamics held at the Langley Aeronautical Laboratory on June 21, 22, and 23, 1948. The conference was held in recognition of the difficulties, imposed by security restrictions, in keeping abreast of the rapid advances in aerodynamics. The papers were prepared to review the status of a number of fields of interest, to summarize the more important wartime advances that are no longer classified, and to orient reference material for further study. The papers in this document are in the same form in which they were presented at the conference so that distribution of them might be prompt. The original presentation and this record are considered as complementary to, rather than as substitutes for, the Committee?s system of complete and formal reports.
Date: 1948-06-21/1948-06-23
Partner: UNT Libraries Government Documents Department

Investigation of Suction-Slot Shapes for Controlling a Turbulent Boundary Layer

Description: Note presenting tests of three types of boundary-layer-control suction slots in a two-dimensional diffuser to investigate design criterions and to evaluate the practical minimum total-pressure losses. Testing occurred at a velocity of about 100 feet per second with a boundary layer with a displacement thickness of 0.85 inch and a shape parameter of about 1.8.
Date: June 1947
Creator: Pierpont, P. Kenneth
Partner: UNT Libraries Government Documents Department

An investigation of a thermal ice-prevention system for a cargo airplane IX: the temperature of the wing leading-edge structure as established in flight

Description: Report presenting flight measurements of structure temperatures occurring in the wing outer panel of the airplane in order to improve the design of thermal ice-prevention systems. Results indicate that structure temperatures increased almost in direct proportion with an increase in heated-air temperature.
Date: June 1948
Creator: Schlaff, Bernard A. & Selna, James
Partner: UNT Libraries Government Documents Department

Investigation of some factors affecting comparisons of wind-tunnel and flight measurements of maximum lift coefficients for a fighter-type airplane

Description: Report presenting a full-scale-tunnel investigation to study the effects of time rate of change of angle of attack, idling propeller operation, and Reynolds number on the maximum lift coefficient of a single-engine fighter-type airplane. Flight test measurements of maximum lift coefficient were also made and compared to wind-tunnel data.
Date: June 1948
Creator: Davis, Don D., Jr. & Sweberg, Harold H.
Partner: UNT Libraries Government Documents Department

Hydrodynamic impact loads in smooth water for a prismatic float having an angle of dead rise of 30 degrees

Description: Report presenting an investigation involving a prismatic-float forebody of 30 degrees angle of dead rise subjected to impacts in smooth water as part of a series of impact tests to investigate the effects of angle of dead rise on hydrodynamic loads of floats and hulls. Results indicated that the loads encountered during impacts can be predicted within the limits of experimental accuracy by curves and equations.
Date: June 1947
Creator: Miller, Robert W. & Leshnover, Samuel
Partner: UNT Libraries Government Documents Department

Effect of exhaust pressure on knock-limited performance of an air-cooled aircraft-engine cylinder

Description: Report presenting an investigation to determine the effect of exhaust pressure on the knock-limited performance of an air-cooled aircraft-engine cylinder. Results are presented in the form of curves showing the relation between the ratio of exhaust pressure to inlet-manifold pressure, the inlet-manifold pressure, and the inlet mixture temperature at incipient knock.
Date: June 1948
Creator: Lord, Albert M.; Heinicke, Orville H. & Stricker, Edward G.
Partner: UNT Libraries Government Documents Department

Effect of preignition on cylinder temperatures, pressures, power output, and piston failures

Description: Report presenting an investigation using a cylinder of a V-type liquid-cooled engine to observe the behavior of the cylinder when operated under preignition conditions. The effects of fuel-air ratio, power output, aromatic content of fuel, engine speed, mixture temperature, and preignition source are provided.
Date: June 1948
Creator: Corrington, Lester C. & Fisher, William F.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections

Description: Report presenting theoretical pressure distributions and experimental aerodynamic characteristics at low speeds for a group of NACA four-digit series airfoil sections. Results regarding lift, drag, and pitching moment are provided.
Date: June 1948
Creator: Loftin, Laurence K., Jr. & Cohen, Kenneth S.
Partner: UNT Libraries Government Documents Department

Airfoil in sinusoidal motion in a pulsating stream

Description: From Introduction: "In the present paper, under the same lineaeizing assumptions as are made in the derivation in reference 1 but with the explicit consideration and simplification of the form of the wake extending from the rear of the airfoil, the methods of Theodorsen (reference 2) have been extended to obtain the forces on the airfoil not only at a fixed angle of attack but also in arbitrary motion."
Date: June 1947
Creator: Greenberg, J. Mayo
Partner: UNT Libraries Government Documents Department

Determination of stresses in gas-turbine disks subjected to plastic flow and creep

Description: Report presenting an extension of a finite-difference method to include the computation of disk stresses when plastic flow and creep are considered. The results of numerical examples indicate qualitatively that plastic flow markedly alters the elastic-stress distribution and that, if the amount of creep is small, the effect on stress distribution is also small.
Date: June 1948
Creator: Millenson, M. B. & Manson, S. S.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the effects of concentrated weights on flutter characteristics of a straight cantilever wing

Description: Report presenting results to show the effects on the flutter characteristics of mounting concentrated weights at various positions on an untapered wing model. The moment of inertia, chordwise position of the weight, and spanwise position of the weight were varied. Results regarding the flutter parameters, flutter-speed ratio, flutter-velocity coefficients, and curves of ratio of first-bending frequency to torsion frequency and second-bending frequency to torsion frequency and provided.
Date: June 1948
Creator: Runyan, Harry L. & Sewall, John L.
Partner: UNT Libraries Government Documents Department

Supersonic nozzle design

Description: From Summary: "The theory of supersonic flow in nozzles is discussed, emphasis being placed on the physical rather than the mathematical point of view. Methods, both graphic and analytic, for designed nozzles are described together with a discussion of design factors. In addition, the analysis of given nozzle shapes to determine velocity distribution and possible existence of shock waves is considered."
Date: June 1948
Creator: Crown, J. Conrad
Partner: UNT Libraries Government Documents Department

Effect of steady rolling on longitudinal and directional stability

Description: Report presenting a theoretical investigation of the effects of steady rolling on the longitudinal and directional stability of aircraft. Simplifying assumptions have been made with regard to the longitudinal and lateral motions of the airplane in order to obtain a solution which shows the principal effects of rolling motion.
Date: June 1948
Creator: Phillips, William H.
Partner: UNT Libraries Government Documents Department

Low-speed wind-tunnel investigation of various plain-spoiler configurations for lateral control on a 42 degree sweptback wing

Description: Report presenting a low-speed wind tunnel investigation of an exploratory nature in order to determine a satisfactory location for a spoiler lateral-control device for a sweptback wing. The semispan wing used for the tests had 42 degrees sweepback referred to the wing leading edge and an aspect ratio of 4.01. The best location appeared to be near the trailing edge of the wing, slightly inboard from the wing tip, and skewed with reference to the wing so as to be perpendicular to the free-stream air flow.
Date: June 1948
Creator: Schneiter, Leslie E. & Watson, James M.
Partner: UNT Libraries Government Documents Department