National Advisory Committee for Aeronautics (NACA) - 11 Matching Results

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Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Description: "An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 f… more
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties

Description: Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.
Date: July 8, 1952
Creator: Black, John M. & Blomquist, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet

Description: Report presenting an experimental investigation of thrust augmentation of an axial-flow-type turbojet engine with a 4000-pound-thrust rating using a water-alcohol injection at the compressor inlet at sea-level conditions and zero ram. Three injection systems were investigated in order to obtain satisfactory atomization and distribution of the injected liquids. Results regarding engine performance and engine operation are provided.
Date: July 8, 1948
Creator: Baron, Burnett; Dowman, Harry W. & Dackis, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flow Diffusion in a Constant-Diameter Duct Downstream of an Abruptly Terminated Center Body

Description: Report presenting an investigation of the flow properties of a constant-outer-wall annual diffuser in combination with a tailpipe in order to come up with a configuration suitable for turbojet afterburners. Information about axial inlet flow and whirling inlet flow is provided. During testing, a vena contrata region formed downstream from the center body terminal and rendered the first 1/2 diameter of the tailpipe ineffective.
Date: July 8, 1953
Creator: Wood, Charles C. & Higginbotham, James T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: Longitudinal Stability and Control of the D-558-1

Description: Report presenting the results of pitching-moment and lift measurements on a model of the D-558-1 airplane with no nose-inlet flow at several tail and elevator settings at a range of Mach numbers. Information about the stability, control, and downwash results is provided.
Date: July 8, 1948
Creator: Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Investigation of the the Take-Off Characteristics of a 1/10-Scale Dynamic Model of the Convair XF2Y-1 Airplane

Description: "An investigation was made of the take-off characteristics of a 1/10-scale dynamic model of the Convair XF2Y-1 airplane. This airplane is a water-based, jet-propelled, delta-wing fighter incorporating a hydro-ski landing gear. Tests were made with the original configuration, with the beaching wheels removed, and with the wheels installed and fairings added in front of the wheels" (p. 1).
Date: July 8, 1954
Creator: McBride, Ellis E. & Fisher, Lloyd J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Notes on Geared Tabs at Supersonic Speeds

Description: Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.
Date: July 8, 1948
Creator: Tucker, Warren A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2

Description: "The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed … more
Date: July 8, 1948
Creator: Mottard, Elmo J. & Ruggles, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of the NACA 64-010 and 64A010 Airfoil Sections at High Subsonic Mach Numbers

Description: Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.
Date: July 8, 1949
Creator: Hemenover, Albert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The transonic characteristics of 38 cambered rectangular wings of varying aspect ratio and thickness as determined by the transonic-bump technique

Description: Report presenting an investigation to determine the effects of camber on the aerodynamic characteristics of a series of rectangular wings with various aspect ratios and thickness-to-chord ratios using the transonic-bump method. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching-moment characteristics are presented for wings of 5 aspect ratios, NACA 63A2XX and 63A4XX sections, and 5 thickness-to-chord ratios.
Date: July 8, 1952
Creator: Nelson, Warren H. & Krumm, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing

Description: Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.
Date: July 8, 1953
Creator: Phelps, E. Ray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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