5,164 Matching Results

Search Results

Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an experimental investigation made in the supersonic flutter tunnel to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing over a range of Mach numbers. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Partner: UNT Libraries Government Documents Department

Interferometric observation of flow about an isentropic (reverse Prandtl-Meyer streamline) compression wedge at Mach 3.0

Description: Report presenting an interferometric study of the flow over a two-dimensional isentropic compression surface at a Mach number of 3.0. The flow field was essentially that of a strong-branch-shock configuration resulting from a surface flow turning that corresponded to an empirical limiting value of free-stream normal-shock pressure rise.
Date: March 28, 1955
Creator: Connors, James F.; Woollett, Richard R. & Blue, Robert E.
Partner: UNT Libraries Government Documents Department

Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 1: design of vortex turbine and performance with stator at design setting

Description: Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and operational requirements are provided.
Date: May 25, 1954
Creator: Heaton, Thomas R.; Forrette, Robert E. & Holeski, Donald E.
Partner: UNT Libraries Government Documents Department

An investigation of a method for obtaining hydrodynamic data at very high speeds with a free water jet

Description: Report presenting information regarding the feasibility of using a rectangular free water jet to obtain hydrodynamic data at very high speeds. Total-head pressure distributions in the jet and experimental hydrodynamic lift data is provided and compared to data obtained in water tank testing. The data obtained indicates that it is feasible to use a free water jet for this purpose.
Date: June 14, 1954
Creator: Weinflash, Bernard & McGehee, John R.
Partner: UNT Libraries Government Documents Department

Investigation of a ram-jet-powered helicopter rotor on the Langley helicopter test tower

Description: Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.
Date: June 3, 1953
Creator: Carpenter, Paul J. & Radin, Edward J.
Partner: UNT Libraries Government Documents Department

Investigation of a tilting-wing vertical-take-off-and-landing jet airplane model in hovering and transition flight

Description: Report presenting the results of an investigation of the dynamic stability and controllability of a proposed supersonic-cruise, vertical-take-off-and-landing airplane configuration with a tilting wing and engines. The configuration tested was found to have satisfactory take-off, landing, and hovering characteristics. Information about transition flight, including stability and control characteristics, is provided.
Date: August 26, 1958
Creator: Kirby, Robert H. & Hassell, James L., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of a transonic turbine designed for a maximum rotor-blade suction-surface relative Mach number of 1.57

Description: From Summary: "A transonic turbine designed for a maximum blade-surface relative Mach number of 1.57 was investigated experimentally. The performance of the turbine is compared with that of three other transonic turbines that were previously investigated."
Date: October 11, 1954
Creator: Whitney, Warren J.; Wong, Robert Y. & Monroe, Daniel E.
Partner: UNT Libraries Government Documents Department

Investigation of adjustable supersonic inlet in combination with J34 engine up to Mach 2.0

Description: Report presenting an investigation of an annular nose inlet equipped with a remotely controlled translating spike and variable bypass in the supersonic wind tunnel. The inlet performance was explored with the airflow controlled by an operating J34 engine and with the engine simulated by a choked plug. Results regarding the performance of the inlet, corrective action that should be applied to avoid pulsing, performance of the subsonic portion of the diffuser, supersonic performance, radial-flow profiles, and other flow profiles are provided.
Date: October 15, 1954
Creator: Nettles, J. C. & Leissler, L. A.
Partner: UNT Libraries Government Documents Department

Investigation of a 10-stage subsonic axial-flow research compressor 3: investigation of rotating stall, blade vibration and surge at low and intermediate compressor speeds

Description: Report presenting an investigation of rotating stall and surge at low and intermediate speeds conducted on a 10-stage subsonic axial-flow research compressor. Fluctuations of rotating stall and surge were detected by hot-wire anemometers and pressure transducers. Results regarding overall performance and rotating stall, rotating stall and blade vibration, surge, and discussion of surge are provided.
Date: May 18, 1953
Creator: Huppert, Merle C.; Costilow, Eleanor L. & Budinger, Ray E.
Partner: UNT Libraries Government Documents Department

Investigation of a high-performance axial-flow compressor transonic inlet rotor designed for 37.5 pounds per second per square foot of frontal area 1: aerodynamic design and overall performance

Description: Report presenting an investigation of the design and tests of a transonic inlet rotor with emphasis placed on increasing the design specific weight flow while maintaining reasonably high pressure ratio and efficiency. Information regarding peak efficiency and how to best achieve it through design is provided.
Date: March 24, 1955
Creator: Savage, Melvyn & Felix, A. Richard
Partner: UNT Libraries Government Documents Department

Investigation of a pulse-jet-powered helicopter rotor on the Langley helicopter test tower

Description: Report discussing testing of a helicopter rotor powered by pulse-jet engines located at the rotor-blade tips. The basic hovering characteristics of the rotor and propulsive characteristics of the pulse-jet engine were obtained at a range of engine speeds with the engines rigidly fixed to the blade tips and with the engines free to pivot. Measurements were also taken to determine the effect of inlet blockage on the power-off drag of the jet engines and the noise intensity in the vicinity of operating engines.
Date: February 8, 1954
Creator: Radin, Edward J. & Carpenter, Paul J.
Partner: UNT Libraries Government Documents Department

Investigation of a high-performance axial-flow compressor transonic inlet rotor designed for 37.5 pounds per second per square foot of frontal area: detailed blade-element performance

Description: Report presenting detailed blade-element-performance plots for a high-flow transonic inlet rotor. Information provided includes the effects of Mach number, blade loading, and angle of attack on element performance is provided.
Date: April 12, 1957
Creator: Felix, A. Richard & Savage, Melvyn
Partner: UNT Libraries Government Documents Department

Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 2: performance of vortex turbine at various stator settings

Description: Report presenting a consideration of a mode of engine operation that requires operational flexibility of the turbine, which requires that the turbine stator and exhaust nozzle area are adjusted to maintain a fixed compressor operating point. Results regarding turbine performance and comparison of predicted and experimental turbine performance are provided.
Date: August 3, 1954
Creator: Heaton, Thomas R.; Holeski, Donald E. & Forrette, Robert E.
Partner: UNT Libraries Government Documents Department

Internal-Film Cooling of Rocket Nozzles

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.
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Partner: UNT Libraries Government Documents Department

Investigation of a high-flow transonic-compressor inlet stage having a hub-tip radius of 0.35

Description: Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.
Date: March 6, 1958
Creator: Felix, A. Richard
Partner: UNT Libraries Government Documents Department

Investigation of a missile airframe with control surfaces consisting of projecting quadrants of the nose cone

Description: Report presenting the results of an investigation of a missile model with extensible control surfaces and small-span fins. Normal-force, axial-force, and pitching-moment coefficients based on body cross-sectional area and diameter are given for various control deflections up to a maximum of 30 degrees.
Date: March 15, 1954
Creator: Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department

Investigation of a 1/22-scale model of the Republic F-105 airplane in the Langley 8-foot transonic tunnel: static longitudinal stability and control and performance characteristics at transonic speeds

Description: Report presenting an investigation of the aerodynamic characteristics of various configurations of a model of the Republic F-105 in the transonic tunnel at a variety of Mach numbers. Results regarding lift characteristics, pitching-moment characteristics, zero-lift drag characteristics, maximum lift-drag ratio, flaperon and rudder characteristics, and effective downwash characteristics are provided.
Date: April 26, 1956
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department

Investigation of a 10-stage subsonic axial-flow research compressor: II: preliminary analysis of overall performance

Description: Report presenting an investigation of the overall performance of a 20-inch-tip-diameter 10-stage compressor as the initial step to examine the problems encountered in an axial-flow compressor with a high pressure ratio per stage. The investigation was carried out over a range of weight flows and percentages of the design speed. Results regarding the part-speed efficiency, surge characteristics, overspeed characteristics, compressor discharge Mach number, and stage characteristics are provided.
Date: June 16, 1952
Creator: Budinger, Ray E. & Thomson, Arthur R.
Partner: UNT Libraries Government Documents Department

Investigation of a canard missile configuration (NACA RM-4) in the Langley 9-inch supersonic tunnel at Mach numbers of 1.62 and 1.93

Description: Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.
Date: June 24, 1954
Creator: Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department

Investigation of high-temperature operation of liquid-cooled gas turbines I: turbine wheel of aluminum alloy, a high-conductivity nonstrategic material

Description: Report presenting an investigation of turbine operating temperatures as affected by liquid cooling, especially if materials of high conductivity are used, at gas temperatures up to 1925 degrees Fahrenheit. Results regarding the statio heat-transfer rig and turbine rig are provided. The investigation showed that nonstrategic material such as aluminum alloy can be used in liquid-cooled turbine wheels at high gas temperatures.
Date: July 22, 1948
Creator: Kottas, Harry & Sheflin, Bob W.
Partner: UNT Libraries Government Documents Department

Investigation of interference lift, drag, and pitching moment of a series of triangular wing and body combinations at a Mach number of 1.62

Description: Report presenting an investigation at Mach number 1.62 of a series of triangular wing and body combinations to determine the interference lift, drag, and pitching moment. Testing was conducted on seven flat-plate triangular wings of varying scale, four with a half-apex angle of 30 degrees and three with a half-apex angle of 45 degrees. Results regarding wing alone, wing in the presence of the body, basic quantities for interference evaluation, interference quantities, and contributions of both types of quantities are provided.
Date: May 27, 1955
Creator: Coletti, Donard E.
Partner: UNT Libraries Government Documents Department

A method for rapid selection of design characteristics of 1-, 1 1/2-, and 2-stage turbines with optimum annulus taper

Description: Report presenting a method for the rapid selection of a turbine design within specified aerodynamic limits. Tables are provided with the overall design parameters and velocity-diagram variables of each design. Detailed design information is also included for ranges of blade-speed parameter and exit radius ratio.
Date: February 18, 1958
Creator: Yohner, Peggy L. & English, Robert E.
Partner: UNT Libraries Government Documents Department

Wing load distribution on a swept wing airplane in flight at Mach numbers up to 1.11, and comparison with theory

Description: Report presenting flight tests to determine the pressure distribution over the wing of a swept-wing jet-propelled airplane over the flight range of lift coefficients for Mach numbers up to 1.11. Results regarding the section characteristics, load distribution, and trailing-edge loads are provided.
Date: April 14, 1952
Creator: Rolls, L. Stewart & Matteson, Frederick H.
Partner: UNT Libraries Government Documents Department

Variation of pressure limits of flame propagation with tube diameter for various isooctane-oxygen-nitrogen mixtures

Description: An investigation was made of the change in the pressure limits of flame propagation with tube diameter for various isooctane-oxygen-nitrogen mixtures. Pressure limits were measured in cylindrical glass tubes of four different inside diameters at six different oxygen-nitrogen ratios. Under the experimental conditions, flame propagation was found to be impossible in isooctane-oxygen mixtures with oxygen concentrations less than 11 to 12 percent. Critical tube diameters for flame propagation were calculated and the effect of pressure was determined and compared with the effect of pressure on quenching distance. Critical diameters were related to flame speeds for various isooctane-oxygen-nitrogen mixtures.
Date: March 3, 1952
Creator: Spakowski, Adolph E. & Belles, Frank E.
Partner: UNT Libraries Government Documents Department