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Technical Report Archive and Image Library
145
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88
TRAIL Microcard Collection
28
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23
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13
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2
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53
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28
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26
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21
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184 Matching Results
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Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3
Report presenting the results of a free-flight investigation to determine the drag of circular, finite-length cylinders for a range of Mach numbers. For supersonic speeds, the drag of circular cylinders was found to be largely independent of fineness ratio and Reynolds number.
Date:
June 16, 1952
Creator:
Welsh, Clement J.
Object Type:
Report
System:
The UNT Digital Library
An investigation of the subsonic speed range of a full-span and a semispan model of a plane wing and of a cambered and twisted wing, all having 45 degrees of sweepback
Report presenting a wind-tunnel investigation of two full-span and two semispan models with 45 degrees of sweepback, an aspect ratio of 5.5, and a taper ratio of 0.53. The lift and drag data obtained from tests of the semispan agreed well with data obtained on the full-span model. Results regarding a comparison of the data for the full-span and semispan models, full-span model data, and effect of surface roughness are provided.
Date:
June 26, 1952
Creator:
Shibata, Harry H.; Bandettini, Angelo & Cleary, Joseph
Object Type:
Report
System:
The UNT Digital Library
An analysis of axial- and centrifugal-flow turbojet-engine performance with variable-area exhaust nozzle
From Introduction: "The purpose of this report is to compare the effect on engine performance of the variable-area exhaust nozzle for axial- and centrifugal-flow turbojet engines."
Date:
June 19, 1952
Creator:
Barson, Zelmar
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of air-cooled turbine blades in turbojet engine 11: internal-strut-supported rotor blade
Report presenting an investigation of an air-cooled internal-strut-supported blade in a modified production turbojet engine to determine the cooling effectiveness of this type of blade and the cooling-air pressure loss through the blade under engine operating conditions. Experimental results are presented and compared with the results of an analytical investigation.
Date:
June 2, 1952
Creator:
Cochran, Reeves P.; Stepka, Francis S. & Krasner, Morton H.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Axial-Flow Compressor Stator Blades Designed to Obtain High Turning Angles by Means of Boundary-Layer Suction
Memorandum presenting an investigation to determine the practicability of using blade boundary-layer control in order to obtain high turning angles in a stator-blade row. The overall performance of the stage was obtained for a range of weight flows at each of three tip speeds with and without hub section. Results regarding slot configuration, overall performance, and stator-blade wakes are provided.
Date:
June 27, 1952
Creator:
Costello, G. R.; Cummings, R. L. & Serovy, G. K.
Object Type:
Report
System:
The UNT Digital Library
Investigation of lift and center of pressure of low-aspect-ratio, cruciform, triangular, and rectangular wings in combination with a slender fuselage at high supersonic speeds
Report presenting tests to evaluate the usefulness of available theory for the calculation of lift-curve slope and center of pressure of low-aspect-ratio, triangular, and rectangular cruciform wings in combination with a long slender body. Tests were made over a range of Mach and Reynolds numbers based on model length.
Date:
June 26, 1952
Creator:
Canning, Thomas N. & Denardo, Billy Pat
Object Type:
Report
System:
The UNT Digital Library
Effect of fuel properties on carbon deposition in atomizing and prevaporizing turbojet combustors
Report presenting investigations of the effects of fuel properties on combustion-chamber carbon deposition in singe tubular fuel-atomizing and fuel-prevaporizing combustors. The NACA K factor and the smoking tendency were approximately equally effective in relating carbon-deposition data from the prevaporizing and atomizing combustors. Results regarding the K factor, smoking tendency, effect of prevaporizing combustor operating conditions, sulfur, gum, and olefin, are provided.
Date:
June 6, 1952
Creator:
Wear, Jerrold D. & Cook, William P.
Object Type:
Report
System:
The UNT Digital Library
Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket
Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.
Date:
June 17, 1952
Creator:
Abramson, Andrew E.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation From Mach Number 0.8 to 2.0 to Determine Some Effects of Wing-to-Tail Distance on the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Canard Missile
Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effect on minimum drag.
Date:
June 20, 1952
Creator:
Brown, Clarence A., Jr. & Lundstrom, Reginald R.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 2: blade-coordinate data
"Supplementary blade-design data including rotor- and stator-blade coordinates and mean-line angles at the leading and the trailing edges are presented for a transonic axial-flow compressor inlet stage" (p. 1).
Date:
June 6, 1952
Creator:
Lewis, George W., Jr.
Object Type:
Report
System:
The UNT Digital Library
A study of the flow over a 45 degree sweptback wing-fuselage combination at transonic Mach numbers
Report presenting pressure distributions, tuft patterns, and schileren surveys of a sweptback wing-fuselage combination in the 8-foot transonic tunnel at a range of Mach numbers and angles of attack. The wing had 45 degrees of sweepback, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Results regarding an angle of attack of 0 degrees, 4 degrees, 6 degrees, 8 degrees, 12 degrees, and 20 degrees are provided.
Date:
June 25, 1952
Creator:
Whitcomb, Richard T. & Kelly, Thomas C.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Survey of Boundary-Layer Development at a Nominal Mach Number of 5.5
Memorandum presenting a measurement of the mean skin-friction coefficients on a flat-plate model, with and without initial roughness, and on a wind tunnel wall were measured at a nominal Mach number of 5.5 over a range of Reynolds numbers.
Date:
June 18, 1952
Creator:
Bloom, Harold L.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Stage Matching and Off-Design Performance of Multistage Axial-Flow Compressors
From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."
Date:
June 27, 1952
Creator:
Finger, Harold B. & Dugan, James F., Jr.
Object Type:
Report
System:
The UNT Digital Library
Pressure drop in coolant passages of two air-cooled turbine-blade configurations
Report presenting pressure and temperature changes in the cooling air flowing through air-cooled gas-turbine blades, which have been measured experimentally in a static cascade on a 10-tube blade for isothermal and nonisothermal flows, and on a 13-fine blade for isothermal flows. Values of pressure and temperature were obtained for a range of cooling-air flows over a range of Reynolds numbers, Mach numbers, and heat-transfer rates.
Date:
June 17, 1952
Creator:
Brown, W. Byron & Slone, Henry O.
Object Type:
Report
System:
The UNT Digital Library
An Analytical Study of the Comparative Performance of Four Air-Induction Systems for Turbojet-Powered Airplanes Designed to Operate at Mach Numbers Up to 1.5
Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.
Date:
June 17, 1952
Creator:
Blackaby, James R.
Object Type:
Report
System:
The UNT Digital Library
Some stress rupture and creep properties of molybdenum disilicide in the range of 1600 to 2000 F
Report presenting an investigation of the stress-rupture and creep properties of hot-pressed molybdenum disilicide, which explored the stress-rupture properties, use of molybdenum disilicide at various temperatures, long-time strength, and a satisfactory method for creep and stress-rupture testing.
Date:
June 24, 1952
Creator:
Maxwell, W. A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21
Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.
Date:
June 23, 1952
Creator:
Yaker, Charles; Garrett, Floyd B. & Sikora, Paul F.
Object Type:
Report
System:
The UNT Digital Library
An experimental investigation of the zero-lift pressure distribution over a wedge airfoil in closed, slotted, and open-throat tunnels at transonic Mach numbers
Report presenting pressure distributions and Schileren photographs of the flow around a 10-percent-thick diamond airfoil at zero lift in two-dimensional closed, slotted, and open-throat tunnels. Results regarding the effect of slot area ratio and effect of slot spacing are provided.
Date:
June 16, 1952
Creator:
Nelson, William J. & Bloetscher, Frederick
Object Type:
Report
System:
The UNT Digital Library
Supplementary Bibliography of NACA Reports Related to Instrumentation and Research Techniques
Memorandum listing NACA reports related to a variety of research topics, including instruments, research equipment, and research techniques.
Date:
June 19, 1952
Creator:
The Division of Research Information
Object Type:
Report
System:
The UNT Digital Library
Investigation of heat-transfer coefficients in an afterburner
Report presenting an evaluation of the relative importance of heat-transfer modes in an experimental afterburner. The convective heat-transfer coefficients near the combustion-chamber outlet were determined and the effects of three radial distributions of afterburner fuel across the turbine-outlet annulus on the convective heat-transfer coefficient were examined.
Date:
June 27, 1952
Creator:
Koffel, William K. & Kaufman, Harold R.
Object Type:
Report
System:
The UNT Digital Library
Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor tip-speed 2: velocity-diagram study of turbine for engine operation with constant exhaust-nozzle area
Report presenting an investigation of whether or not a two-stage turbine with the frontal area no larger than the compressor frontal area could be satisfactorily designed to drive a particular compressor under take-off conditions. The low blade-tip speed, high work, and high air flow per unit of frontal area of the compressor make it critical that a two-stage turbine is designed to drive it. Results regarding the effect of work division, effect of variation in cone angle, and effects of radial variations on velocity diagrams are provided.
Date:
June 19, 1952
Creator:
Davison, Elmer H. & English, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers
From Summary: "Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9."
Date:
June 19, 1952
Creator:
Gowen, Forrest E. & Perkins, Edward W.
Object Type:
Report
System:
The UNT Digital Library
A preliminary gust-tunnel investigation of leading-edge separation on swept wings
Report presenting the results of a series of qualitative studies with tufts on three wings with sweepback angles of 30 degrees, 45 degrees, and 60 degrees, which show that under certain conditions, a leading-edge vortex can exist in the unsteady flow associated with a gust. The results indicated that if a wing in steady flight prior to entering a gust is at an angle of attack several degrees less than that at which vortex flow first begins in steady flow, it may penetrate the gust without having the vortex develop, even if its angle of attack is increased by the gust into the vortex-flow regime.
Date:
June 6, 1952
Creator:
Cahen, George L.
Object Type:
Report
System:
The UNT Digital Library
Empirical cooling correlation for an experimental afterburner with an annular cooling passage
Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.
Date:
June 26, 1952
Creator:
Koffel, William K. & Kaufman, Harold R.
Object Type:
Report
System:
The UNT Digital Library