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112
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60
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31
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29
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24
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1
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42
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17
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11
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168 Matching Results
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Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine
Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficiencies, and operation in the surge region are provided.
Date:
April 28, 1953
Creator:
Rebeske, John J., Jr. & Dugan, James F., Jr.
Object Type:
Report
System:
The UNT Digital Library
Damping in Pitch of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds
Memorandum presenting the application of the concept of indicial functions to the analysis of the aerodynamic phenomena associated with the short-period pitching mode of wings in subsonic and supersonic flight. Simple physical relationships are pointed out and are used to study the effect on the rotary-damping-moment coefficient of changes in center-of-gravity position, Mach number, aspect ratio, plan form, frequency, and thickness.
Date:
April 8, 1953
Creator:
Tobak, Murray
Object Type:
Report
System:
The UNT Digital Library
Langley full-scale-tunnel tests of the Custer Channel Wing airplane
Memorandum presenting testing of an experimental Custer Channel Wing airplane in the full-scale tunnel to investigate the lift characteristics of a channel-propeller combination and the flow phenomena in and about a channel wing.
Date:
April 7, 1953
Creator:
Pasamanick, Jerome
Object Type:
Report
System:
The UNT Digital Library
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail: Longitudinal and lateral characteristics
Report presenting an investigation to determine the low-speed large-scale characteristics of an aspect ratio 3 triangular-wing airplane model. The model consisted of the wing in combination with a fuselage of fitness ratio 12.5, a thin, triangular vertical tail with a constant-chord rudder, and a thin, unswept, all-movable tail.
Date:
April 13, 1953
Creator:
Koenig, David G.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube
From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."
Date:
April 9, 1953
Creator:
Deissler, Robert G. & Taylor, Maynard F.
Object Type:
Report
System:
The UNT Digital Library
Some torsional-damping measurements of laminated beams as applied to the propeller stall-flutter problem
The structural damping in the torsion mode of vibration of a series of untwisted, laminated thin beams simulating propeller blades is presented. The number of lamination were varied, as well as the bonding material and the method of joining lamination. Application of the data to the calculation of the minimum flutter speed of thin propeller blades indicates that appreciable gains in the minimum flutter speed may be obtained for laminated blades using a Cycleweld bond.
Date:
April 29, 1953
Creator:
Heath, Atwood R., Jr.
Object Type:
Report
System:
The UNT Digital Library
Free-flight tests of three 1/9-scale models of the wing-ram-jet configuration of the Grumman XSSM-N-6A (Rigel) missile to investigate the possibility of flutter: TED No. NACA DE 223
Report presenting cold-flow free-flight tests at zero lift to investigate the possibility of flutter of simulated wing-ram-jet-nacelle configurations which were 1/9-scale models of the wing and ramjet nacelles of the Grumman XSSM-N-6a missile. Testing was performed on three different configurations. Results regarding Mach number, velocity, aerodynamic density, and flutter are provided.
Date:
April 14, 1953
Creator:
O'Kelly, Burke R. & Lauten, William T., Jr.
Object Type:
Report
System:
The UNT Digital Library
Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model
Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.
Date:
April 7, 1953
Creator:
Matthews, Clarence W.
Object Type:
Report
System:
The UNT Digital Library
A method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow
From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."
Date:
April 7, 1953
Creator:
Robinson, Samuel W., Jr. & Zlotnick, Martin
Object Type:
Report
System:
The UNT Digital Library
Effect of Capture on the Slowing-Down Length of Neutrons in Hydrogenous Mixtures Containing Uranium
Memorandum presenting a rigorous expression for the slowing-down length of neutrons in hydrogenous media under the assumption that the nonhydrogen nuclei have infinite mass and that capture is absent. Two expressions have been applied to the same sample mixture, a uranium-235 and water mixture with the ratio of hydrogen to uranium nuclei chosen as 25.
Date:
April 1953
Creator:
Volkin, H. C. & Soffer, L.
Object Type:
Report
System:
The UNT Digital Library
Design procedure and limited test results for a high solidity, 12-inch transonic impeller with axial discharge
Report presenting an approximate inverse impeller design procedure based on the assumption of axisymmetric, nonviscous flow along with some limited experimental data obtained from a high solidity, 12-inch transonic impeller. The design procedure includes a point-by-point solution of the impeller flow conditions along a series of streamlines in the radial-axial plane. Results regarding the overall performance, impeller flow limits, and blade structural failure are provided.
Date:
April 9, 1953
Creator:
Wright, Linwood C. & Kovach, Karl
Object Type:
Report
System:
The UNT Digital Library
Use of flame-immersed blades to improve combustion limits and efficiency of a 5-inch diameter connected-pipe, ram-jet combustor
Report presenting the effects of flame-immersed blades on combustion stability and efficiency, which were determined at various combustor-inlet conditions by use of several geometric blade arrangements, two fuels, two fuel-injection systems, and two blade temperatures. Specific combustor configurations with flame-immersed blades showed marked improvement in stability and efficiency. The operational life of the blades was also observed to be excellent.
Date:
April 9, 1953
Creator:
Male, Donald W.
Object Type:
Report
System:
The UNT Digital Library
An Experimental Investigation of the Zero-Lift-Drag Characteristics of Symmetrical Blunt-Trailing-Edge Airfoils at Mach Numbers From 2.7 to 5.0
Report presenting an investigation of the zero-lift-drag characteristics of nine symmetrical airfoils at a range of Mach and Reynolds numbers. Results regarding pressure and force data are also provided.
Date:
April 29, 1953
Creator:
Syvertson, Clarence A. & Gloria, Hermilo R.
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Aileron Effectiveness as Determined by Force Tests and Visual-Flow Observations on a 52 Degree Sweptback Wing With and Without Chord-Extensions
The results of an investigation of the effects of leading-edge chord-extensions and extensible leading-edge flaps on the low-speed aileron characteristics of a 52 degrees sweptback wing with circular-arc airfoil sections are presented. A description and illustrations of the vortex flow as it passes over the wing are included. The investigation was conducted at Reynolds numbers of 5.5 times 10(exp 6) and 1.3 times 10(exp 6) and corresponding Mach numbers of 0.11 and 0.065 for an angle-of-attack range of 0 degrees through stall.
Date:
April 29, 1953
Creator:
Cancro, Patrick A.
Object Type:
Report
System:
The UNT Digital Library
Large-scale flight measurements of zero-lift drag and low-lift longitudinal characteristics of a diamond-wing-body combination at Mach numbers from 0.725 to 1.54
Report presenting a large-scale diamond-wing-body configuration flown at a range of Mach and Reynolds numbers. The model had a diamond-plan-form wing with an NACA 65A003 airfoil section, a total aspect ratio of 2.31, and 0 degrees sweep of the midchord. Results regarding zero-lift drag and low-lift longitudinal characteristics are provided.
Date:
April 20, 1953
Creator:
Wallskog, Harvey A. & Morrow, John D.
Object Type:
Report
System:
The UNT Digital Library
A Theoretical Study of the Effect of Control-Deflection and Control-Rate Limitations on the Normal Acceleration and Roll Response of a Supersonic Interceptor
Memorandum presenting a theoretical study of the effect of limiting the deflection and rate of deflection of the control surface on the normal acceleration and roll response to step commands for a representative, automatically controlled, supersonic, tailless interceptor. Results regarding pitch, roll, and some general comments are provided.
Date:
April 29, 1953
Creator:
Matthews, Howard F. & Schmidt, Stanley F.
Object Type:
Report
System:
The UNT Digital Library
A Theoretical Analysis of the Distortion of Fuel-Spray-Particle Paths in a Helicopter Ram-Jet Engine Due to Centrifugal Effects
Report presenting a theoretical study of certain anomalies in the behavior of a ram-jet engine engine tip-mounted on a rotating helicopter blade that appears to be related to centrifugal effects distorting the fuel-spray pattern. Results regarding the cases calculated, results of the calculations, particle-path distortion, and limiting direction of particle paths are provided.
Date:
April 7, 1953
Creator:
Katzoff, S. & Smith, Samuel L., III
Object Type:
Report
System:
The UNT Digital Library
Effect of fuel injectors and liner design on performance of an annular turbojet combustor with vapor fuel
Report presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5-inch-diameter annular combustor that had been developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.
Date:
April 6, 1953
Creator:
Norgren, Carl T. & Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Investigation of Pressure Recovery of a Single-Conical-Shock Nose Inlet at Mach Number 5.4
An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.
Date:
April 6, 1953
Creator:
Bernstein, Harry & Haefeli, Rudolph C.
Object Type:
Report
System:
The UNT Digital Library
Effects of slot size and geometry on the flow in rectangular tunnels at Mach numbers up to 1.4
Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.
Date:
April 7, 1953
Creator:
Nelson, William J. & Cubbage, James M., Jr.
Object Type:
Report
System:
The UNT Digital Library
Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches
From Introduction: "A theoretical investigation was conducted in order to determine what effect the differences in aerodynamic characteristics would have on the short-time response to elevator control of this type of airplane as compared with the responses of a conventional airplane, without regard to any possible psychological influences. The results of this investigation are presented in this paper."
Date:
April 9, 1953
Creator:
Bihrle, William, Jr. & Stone, Ralph W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effect of Fuel-Air Ratio Concentration in Combustion Zone on Combustion Performance of a 16-Inch Ram-Jet Engine
The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inch ram-jet combustor indicated that the distribution of combustible mixture immediately downstream of a flame holder should be mechanically controlled if a preferred mixture composition is to be maintained in that zone. A sloping-baffle combustor configuration gave combustion efficiencies of 90 percent or greater over a range of fuel-air ratios from 0.010 to 0.045.
Date:
April 13, 1953
Creator:
Cervenka, A. J.; Bahr, D. W. & Dangle, E. E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 4: Individual Stage Performance Characteristics
Report presenting a determination of the individual stage performance for a 10-stage axial-flow compressor from circumferentially fixed radial rake measurements of total temperature and total pressure obtained at the discharge of each stage. Results regarding compressor performance, stage performance, and some general remarks are provided.
Date:
April 28, 1953
Creator:
Budinger, Ray E. & Serovy, George K.
Object Type:
Report
System:
The UNT Digital Library
The Design of Brittle-Material Blade Roots Based on Theory and Rupture Tests of Plastic Models
"Theoretical design charts based on Neuber's equations for symmetrically located notches are presented for estimating the approximate rupture strengths of blade roots made from brittle materials. The limit of applicability of the theoretical charts is shown as determined by rupture tests of plastic models. The optimum proportions among over-all root width, neck width, notch radius, and notch depth are determined from the design charts" (p. 1).
Date:
April 6, 1953
Creator:
Meyer, André J., Jr.; Kaufman, Albert & Caywood, William C.
Object Type:
Report
System:
The UNT Digital Library