Resource Type
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Serial/Series Title
NACA Research Memorandums
29
NACA Technical Notes
19
Atomic Energy Commission Reports
12
Hanford Works Reports
8
ORNL (Series)
4
Oak Ridge National Laboratory Reports
4
University of California Radiation Laboratory Reports
4
Battelle Memorial Institute Reports
3
NACA Technical Reports
3
RME
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The Plum Island Animal Disease Laboratory.
Examines the research facilities at the Plum Island Animal Disease Laboratory and provides information regarding its location, the organization, and the types of research and service provided.
Date:
September 1956
Creator:
United States. Agricultural Research Service. Animal Disease and Parasite Research Branch.
Object Type:
Book
System:
The UNT Digital Library
Development of Dumont Photomultiplier Tubes: Report Number 19
Report concerning the ongoing development of the Dumont photomultiplier tube. Ongoing improvements have been noted.
Date:
September 1956
Creator:
Linden, B. R.; Snell, P. A. & Schenkel, F. W.
Object Type:
Report
System:
The UNT Digital Library
Development of Dumont Photomultiplier Tubes: Report Number 20
Report concerning the ongoing development of the Dumont photomultiplier tube. Tube improvements have been noted.
Date:
September 1956
Creator:
Linden, B. R.; Snell, P. A. & Schenkel, F. W.
Object Type:
Report
System:
The UNT Digital Library
Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber
Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated without any appreciable sacrifice in engine acceleration time.
Date:
September 21, 1956
Creator:
McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
Object Type:
Report
System:
The UNT Digital Library
Minimum Drag of Four Versions of a Swept-Wing Fighter Airplane Obtained From Flight Tests of Rocket-Boosted Models at Mach Numbers From 0.81 to 1.71
Memorandum presenting tests conducted with four specific versions of a swept-wing fighter airplane, which indicate that a large reduction in external-drag coefficient was accomplished by redesigning the original configuration. The forebody modifications, which consisted of a smaller canopy, slimmer nose, and sharper inlet lip, reduced the value of the external-drag coefficient from 0.044 to 0.042 at a Mach number of 1.05 and from 0.042 to 0.040 at a Mach number of 1.28.
Date:
September 7, 1956
Creator:
Hastings, Earl C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Supersonic Investigation of the Lift, Drag, Static Stability, and Hinge-Moment Characteristics of a Rocket-Powered Model of a Ballistic-Missile Configuration
Memorandum presenting a free-flight investigation to determine the lift, drag, static stability, and hinge-moment characteristics of a rocket-powered model of a rocket-powered model of a ballistic-missile configuration at supersonic speeds. The model consisted essentially of a body of fineness ratio 16.9 and a cruciform set of small 60 degree delta fins located approximately 1 body diameter from the base of the body. The model lift and pitching-moment coefficients were nonlinear with angle of attack.
Date:
September 28, 1956
Creator:
Gillespie, Warren, Jr.
Object Type:
Report
System:
The UNT Digital Library
Interaction of Grids With Traveling Shock Waves
Note presenting a study using grids mounted in the path of traveling shock waves in a shock tube. A description of the behavior of the shock waves is provided.
Date:
September 1956
Creator:
Dosanjh, Darshan Singh
Object Type:
Report
System:
The UNT Digital Library
Theoretical calculation of the power spectra of the rolling and yawing moments on a wing in random turbulence
The correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence are calculated. The rolling moments to the longitudinal (horizontal) and normal (vertical) components depend on the spanwise distributions of instantaneous gust intensity, which are taken into account by using the inherent properties of symmetry of isotropic turbulence. The results consist of expressions for correlation functions or spectra of the rolling moment in terms of the point correlation functions of the two components of turbulence.
Date:
September 6, 1956
Creator:
Eggleston, John M. & Diederich, Franklin W.
Object Type:
Report
System:
The UNT Digital Library
Average Properties of Compressible Laminar Boundary Layer on Flat Plate With Unsteady Flight Velocity
The time-average characteristics of boundary layers over a flat plate in nearly quasi-steady flow are determined. The plate may be either insulated or isothermal. The time averages are found without specifying the plate velocity explicitly except that it is positive and has an average value.
Date:
September 5, 1956
Creator:
Moore, Franklin K. & Ostrach, Simon
Object Type:
Report
System:
The UNT Digital Library
Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas
"Compressible and incompressible flow calculations were made of the combustor total-pressure-loss coefficient and liner airflow distribution for tubular turbojet combustors having constant annulus and liner cross-sectional areas along the combustor axis. Information on static and total pressure distribution and liner air-jet entrance angles along the length of the combustor was obtained as an intermediate step in the calculations. The calculations include the effects of heat release, annulus wall friction, and variation in discharge coefficients of the liner wall openings along the combustor" (p. 899).
Date:
September 17, 1956
Creator:
Graves, Charles C. & Grobman, Jack S.
Object Type:
Report
System:
The UNT Digital Library
Finite Span Wings in Compressible Flow
Equations are developed using the source distribution method for the velocity potential function and pressure on thin wings in steady and unsteady motion. Closed form solutions are given for harmonically oscillating wings of general plan form including the effect of the wing wake. Some useful examples are presented in an appendix for arrow, semielliptical, and hexagonal plan form wings.
Date:
September 1956
Creator:
Krasilschchikova, E. A.
Object Type:
Report
System:
The UNT Digital Library
Effect of Wing Height and Dihedral on the Lateral Stability Characteristics at Low Lift of a 45 Deg Swept-Wing Airplane Configuration as Obtained from Time-Vector Analyses of Rocket-Propelled-Model Flights at Mach Numbers from 0.7 to 1.3
From Summary: "Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of three airplane configurations having 45 degree sweptback wings. One model had a high wing; one, a low wing; and one, a high wing with cathedral. The models were otherwise identical. The lateral oscillations of the models resulting from intermittent yawing disturbances were interpreted in terms of full-scale airplane flying qualities and were further analyzed by the time-vector method to obtain values of the lateral stability derivatives."
Date:
September 14, 1956
Creator:
Gillis, Clarence L. & Chapman, Rowe, Jr.
Object Type:
Report
System:
The UNT Digital Library
An Experimental Investigation of Sting-Support Effects on Drag and a Comparison with Jet Effects at Transonic Speeds
"This paper presents the results of an investigation of sting-support interference on afterbody drag at transonic speeds. Stings with varying diameter, cone angle, and cylindrical length were tested at the rear of a model with various afterbody shapes. The data were obtained at an angle of attack of 0 deg. and at Mach numbers from 0.80 to 1.10. It was found that, in general, the addition of a sting caused a drag reduction" (p. 1).
Date:
September 24, 1956
Creator:
Cahn, Maurice S.
Object Type:
Report
System:
The UNT Digital Library
The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10
Report presenting a wind-tunnel investigation to provide data for the study of the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration with a wing of 40 degrees of sweepback and an aspect ratio of 10. Coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are presented in tabular form for various values of advance ratio at constant angles of attack.
Date:
September 1956
Creator:
Edwards, George G.; Dickson, Jerald K.; Sutton, Fred B. & Demele, Fred A.
Object Type:
Report
System:
The UNT Digital Library
Supersonic flow past nonlifting bumped and indented bodies of revolution
Linear-theory values of the supersonic pressure field and wave drag of nonlifting bumped and indented bodies of revolution are presented and compared with the corresponding properties of a smooth body. The comparisons indicate that relatively small surface irregularities cause large pressure disturbances and changes in wave drag. The interference drag produced by bumps and indentations is discussed and a correction for the curvature of the characteristics is applied.
Date:
September 1956
Creator:
McLean, F. Edward & Rennemann, Conrad, Jr.
Object Type:
Report
System:
The UNT Digital Library
Some Observations on the Relationship Between Fatigue and Internal Friction
Results are presented of an investigation made to determine the internal friction and fatigue strength of commercially pure 1100 aluminum under repeated stressing in torsion at various temperatures and stress levels in an effort to find if there exists any correlation between internal friction and fatigue characteristics.
Date:
September 1956
Creator:
Valluri, S. R.
Object Type:
Report
System:
The UNT Digital Library
Some effects of small-scale flow disturbance on nozzle-burner flames
Laminar-like and brush-like propane-air flames were obtained when wire grids were used as turbulence generators in a 1/2-inch nozzle burner. The laminar-like flames for grid-disturbed flow had a slightly higher burning velocity than "true" laminar flames (no grid used). The brush-like flames were similar to those obtained with pipe turbulent flow. Their burning-velocity dependence on a "flow disturbance" Reynolds number compared favorably with that obtained for pipe turbulent flames. Hot-wire-anemometer equipment was used to measure the flow disturbance intensity in the cold flow with and without the grids in place.
Date:
September 1956
Creator:
Wong, Edgar L.
Object Type:
Report
System:
The UNT Digital Library
The use of perforated inlets for efficient supersonic diffusion
Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.
Date:
September 1956
Creator:
Evvard, John C. & Blakey, John W.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Wind-Tunnel Tests to a Mach Number of 0.90 of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
Report presenting an investigation at speeds of up to Mach number 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration with a 40 degree swept wing with an aspect ratio of 10. Results regarding low-speed conditions, high-speed conditions, components of lift, effect of configuration changes, longitudinal stability, and the reduction of adverse effects of propellers on stability are provided.
Date:
September 1956
Creator:
Edwards, George G.; Buell, Donald A.; Demele, Fred A. & Sutton, Fred B.
Object Type:
Report
System:
The UNT Digital Library
Tentative Method for Calculation of the Sound Field About a Source Over Ground Considering Diffraction and Scattering Into Shadow Zones
Note presenting a semiempirical method for the calculation of the sound field about a source over ground considering the effects of vertical temperature and wind gradients as well as scattering of sound by turbulence into shadow zones. The two adjustable parameters in the formula were obtained from measurements suing a relatively small source height.
Date:
September 1956
Creator:
Pridmore-Brown, David C. & Ingard, Uno
Object Type:
Report
System:
The UNT Digital Library
On a Method for Optimization of Time-Varying Linear Systems With Nonstationary Inputs
"By means of examples, a new method is illustrated for optimizing, over a finite interval of time, time-varying systems with stationary or nonstationary statistical inputs. The method depends on the correlation functions being of a certain type, which, fortunately, is the type found in a large number of practical problems of importance" (p. 1).
Date:
September 1956
Creator:
Shinbrot, Marvin
Object Type:
Report
System:
The UNT Digital Library
The Design of Brittle-Material Blade Roots Based on Theory and Rupture Tests of Plastic Models
Report presenting theoretical design charts based on Neuber's equations for symmetrically located notches in order to estimate the approximate rupture strengths of blade roots made from brittle materials. The ideal proportions for overall root width, neck width, notch radius, and notch depth are determined from the design charts. Results regarding notch specimens, blade-root specimens, the blade-root design procedure, practical limit of the design charts, effect of included angle on dovetail root, and effect of additional load-carrying lands are provided.
Date:
September 1956
Creator:
Meyer, André J., Jr.; Kaufman, Albert & Caywood, William C.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base
Report discussing an aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base.
Date:
September 1956
Creator:
Love, Eugene S.
Object Type:
Report
System:
The UNT Digital Library
Turbulent shear spectra and local isotropy in the low-speed boundary layer
"From measurements of turbulent shear spectra together with previously reported longitudinal turbulent energy spectra, the concept of local isotropy in a low-speed boundary layer was examined. Results of these measurements and measurements of the time derivatives of turbulent velocities in the x- and y- directions for various frequency bands showed no evidence of local isotropy in the boundary layer. Several methods (based on isotropy) of evaluating the turbulent dissipation term failed to give consistent answers, further emphasizing a lack of local isotropy" (p. 1).
Date:
September 1956
Creator:
Sandborn, Virgil A. & Braun, Willis H.
Object Type:
Report
System:
The UNT Digital Library