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Preliminary investigation of flow fluctuations during surge and blade row stall in axial-flow compressors

Description: "A preliminary investigation of the flow fluctuations of surge and blade row stall was conducted with three single-stage axial-flow compressors with hub-tip ratios of 0.9,0.8, and 0.5 and with a multistage axial-flow compressor. Flow fluctuations of large amplitude associated with stall were detected in all compressors investigated. The fluctuations were caused by low flow regions affecting 25 to 40 percent of the annulus area and propagating in the direction of compressor rotation, but at a lo… more
Date: August 13, 1952
Creator: Huppert, Merle C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Interference, Lift, Drag, and Pitching Moment of a Series of Rectangular Wing and Body Combinations at Mach Numbers of 1.62, 1.93,and 2.41

Description: Report presenting an investigation of a series of rectangular wing and body combinations at Mach numbers 1.62, 1.93, and 2.41 to determine the effects of aspect ratio, incidence angle, and forebody length on the interference lift, drag, and pitching moment. A limited investigation to determine the effect of Reynolds number on the wings in the presence of the body was also carried out. Information regarding wing lift, basic quantities for interference evaluation, interference qualities, contribu… more
Date: August 13, 1952
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the… more
Date: August 13, 1952
Creator: Abramovitz, Marvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet

Description: Report presenting an experimental investigation to determine the thrust augmentation possible by the injection of liquid ammonia into the compressor inlet of an axial-flow-type turbojet engine. Results regarding the selection of coolant, cooling with liquid ammonia, engine performance, and operating experience are provided.
Date: August 13, 1952
Creator: Harp, James L., Jr.; Useller, James W. & Auble, Carmon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 turbojet combustor

Description: Report presenting an investigation to determine the importance of molecular-scale processes in the overall turbojet combustion process. The effect of oxygen concentration on the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 combustor was determined for a range of combustor-inlet pressures and a range of fuel-flow rates. At a given fuel-flow rate, combustion efficiency decreased at an increasing rate with reduction in oxygen concentration.
Date: August 13, 1952
Creator: Graves, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Characteristics of a 45 Degree Swept Wing with Leading-Edge Inlets

Description: Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 45 degree swept wing with leading-edge inlets. The wing had a constant chord and completely spanned the wind tunnel. Results regarding surface-pressure characteristics, lift and pitching-moment characteristics, wake-drag characteristics, and internal-flow characteristics are provided.
Date: August 13, 1951
Creator: Dannenberg, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic free-flight investigation of the total drag and of the component drags (cowl pressure, additive, base, friction, and internal) encountered by a 16-inch-diameter ram-jet engine for Mach numbers from 0.80 to 1.43

Description: Report presenting an investigation of the drag on four full-scale models of 16-inch-diameter ramjet engines. The total, base, internal, and external drag were evaluated for each of the models. Results regarding the drag evaluations and drag comparison are provided.
Date: August 13, 1952
Creator: Messing, Wesley E. & Rabb, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Forced-convection heat-transfer and pressure-drop characteristics of a closely spaced wire matrix

Description: Memorandum presenting an investigation of the forced-convection heat-transfer and pressure-drop characteristics of a staggered closely spaced 0.020-inch wire metal-to-air heat exchanger. Eight wire banks were electrically heated, and the range of variables included bulk Reynolds numbers based on wire diameter and maximum velocity, from 82 to 1900, average wire temperatures up to 1109 degrees R, and heat flux densities up to 84,000 Btu per hour per square foot.
Date: August 13, 1954
Creator: Gedeon, Louis & Grele, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the behavior of parachutes in close proximity to one another

Description: Memorandum presenting an investigation in which the behavior of parachutes in close proximity to one another was studied by using small parachutes attached to thin wires in the 20-foot free-spinning tunnel. The results indicate that the parachutes, when side by side, generally had little effect on one another and may sometimes have had slight repelling effects.
Date: August 13, 1953
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Engineering method of ram-jet thrust determination based on experimentally obtained combustor parameters

Description: From Summary: "A parameter is introduced which simplifies the accounting for pressure losses in ram-jet combustors. This parameter, called the combustor-force coefficient, relates the jet force and the total pressure at the combustion-chamber entrance. Experimental data for several different combustors are presented for evaluation and comparison."
Date: August 13, 1953
Creator: Dettwyler, H. Rudolph & Faget, Maxime A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of shock diffusers at Mach number 1.85 3: multiple-shock and curved-contour projecting cones

Description: Report presenting total-pressure recoveries obtained with four-cone inlet combinations at Mach number 1.85. The configurations tested included a cone designed to produce three oblique shocks ahead of the diffuser inlet combined with two other inlets, a cone generated by a parabolic arc in combination with two other inlets, a cone-inlet combination designed to produce an isentropic entrance flow at 0 degrees angle of attack, and a 30 degree single-shock cone combined with a perforated inlet sect… more
Date: August 13, 1947
Creator: Moeckel, W. E. & Connors, J. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of Fullspan, 0.2 Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Taper, Aspect Ratio, and Section-Thickness Ratio

Description: Report presenting an aerodynamic-control-effectiveness investigation using free-flight rocket-propelled RM-5 test vehicles at high subsonic, transonic, and supersonic speeds. Results regarding aileron control characteristics and drag measurements are provided.
Date: August 13, 1947
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

Description: Effects of air-cooling turbine rotor blades on performance of a turbojet engine were calculated for a range of altitudes from sea level to 40,000 feet and a range of coolant flows up to 3 percent of compressor air flow, for two conditions of coolant bleed from the compressor. Bleeding at required coolant pressure resulted in a sea-level thrust reduction approximately twice the percentage coolant flow and in an increase in specific fuel consumption approximately equal to percentage coolant flow.… more
Date: August 13, 1951
Creator: Arne, Vernon L. & Nachtigall, Alfred J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. It is shown that, with the antenna stabilized in space, the effect of component lags on the response is small, so that the speed of response is small, so that the speed of response can be made to approach closely that of the airframe alone.
Date: August 13, 1952
Creator: Abramovitz, Marvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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