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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
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
Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)

Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)

Date: June 24, 1948
Creator: Williams, Walter C
Description: Contains a few measurements of the variation of elevator angle and elevator force with Mach number at 30,000 feet altitude up to a Mach number of 0.85. These data show that the airplane possessed positive static longitudinal stability up to a Mach number of 0.80. A trim change in the nose-down direction occurred for Mach numbers above 0.82.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen

Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen

Date: May 26, 1948
Creator: Miller, Riley O & Ordin, Paul M
Description: Theoretical performance data including nozzle-exit temperature, specific impulse, volume specific impulse and composition, temperature, and mean molecular weight of reaction products based on frozen equilibrium and isentropic expansion are presented for 13 propellant combinations at reaction pressure of 300 pounds per square inch absolute and expansion ratio of 20.4. On basis of maximum specific impulse alone, five fuels had the following order for any given oxidant: liquid hydrogen, hydrazine, liquid ammonia, and either hydrazine hydrate or hydroxylamine. Three oxidants with a given fuel had the following order: liquid ozone, liquid oxygen, and 100-percent hydrogen peroxide.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary investigation of combustion in flowing gas with various turbulence promoters

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Date: June 7, 1948
Creator: Haddock, Gordon W & Childs, J Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Date: April 6, 1948
Creator: Williams, W C & Beeler, De E
Description: Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Contributing Partner: UNT Libraries Government Documents Department