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 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model

Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model

Date: December 16, 1948
Creator: Dods, Jules B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

Date: January 7, 1949
Creator: Weinflash, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Date: July 23, 1948
Creator: Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Date: January 12, 1949
Creator: Lockwood, Vernard E; Vogler, Raymond D & Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel II : the effectiveness and hinge moments of a constant-chord plain flap

Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel II : the effectiveness and hinge moments of a constant-chord plain flap

Date: September 21, 1948
Creator: Stephenson, Jack D & Amuedo, Arthur R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of flow conditions and the nature of the wall-constriction effect near and at choking by means of the hydraulic analogy

Investigation of flow conditions and the nature of the wall-constriction effect near and at choking by means of the hydraulic analogy

Date: September 1, 1948
Creator: Wright, Ray H & Matthews, Clarence W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of several air ejectors with conical mixing sections and small secondary flow rates

Performance of several air ejectors with conical mixing sections and small secondary flow rates

Date: July 19, 1948
Creator: Huddleston, S C; Wilsted, H D & Ellis, C W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of a swept-blade propeller and related straight blades having thickness ratios of 5 and 6 percent

Wind-tunnel tests of a swept-blade propeller and related straight blades having thickness ratios of 5 and 6 percent

Date: November 10, 1948
Creator: Gray, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Internal-Film Cooling of Rocket Nozzles

Internal-Film Cooling of Rocket Nozzles

Date: June 8, 1948
Creator: Sloop, J L & Kinney, George R
Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections.
Contributing Partner: UNT Libraries Government Documents Department
Ice protection of turbojet engines by inertia separation of water III : annular submerged inlets

Ice protection of turbojet engines by inertia separation of water III : annular submerged inlets

Date: June 8, 1948
Creator: Von Glahn, Uwe
Description: Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at inlet-velocity ratio of 0.86. All inlets exhibited considerable screen icing. Severe mass-flow shifts occurred at angles of attack.
Contributing Partner: UNT Libraries Government Documents Department
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