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An analysis of once-per-revolution oscillating aerodynamic thrust loads on single-rotation propellers on tractor airplanes at zero yaw

Description: A simplified procedure is shown for calculating the once-per-revolution oscillating aerodynamic thrust loads on propellers of tractor airplanes at zero yaw. The only flow field information required for the application of the procedure is a knowledge of the upflow angles at the horizontal center line of the propeller disk. Methods are presented whereby these angles may be computed without recourse to experimental survey of the flow field. The loads computed by the simplified procedure are compar… more
Date: March 21, 1955
Creator: Rogallo, Vernon L.; Yaggy, Paul F. & McCloud, John L., III
Item Type: Refine your search to only Report
open access

Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines

Description: Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.
Date: April 21, 1955
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
open access

Correlation of turbine-blade-element losses based on wake momentum thickness with diffusion parameter for a series of subsonic turbine blades in two-dimensional cascade and for four transonic turbine rotors

Description: Report presenting an analysis of losses occurring in a series of subsonic turbine blades in a low-speed two-dimensional cascade and in a related series of four transonic rotors. Results regarding the two-dimensional cascade loss correlations, transonic turbine loss correlations, effect of unsteady flows, and mixing of stator wakes are provided.
Date: April 21, 1955
Creator: Wong, Robert Y. & Stewart, Warner L.
Item Type: Refine your search to only Report
open access

Effect of ejector performance of varying diameter ratio by simulated iris flaps

Description: Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel at several free-stream Mach numbers for a range of primary-nozzle pressure ratios and secondary weight-flow ratios to determine the effects on performance of varying the ejector diameter ratio by simulated iris flaps. Results indicated that increases in ejector gross force and secondary-to-primary total-pressure ratio were obtained subsonically when diameter ratio was reduced, thus reducing overexpansion losses.
Date: April 21, 1955
Creator: Valerino, Alfred S. & Stitt, Leonard E.
Item Type: Refine your search to only Report
open access

The effect of fluid injection on the compressible turbulent boundary layer: preliminary tests on transpiration cooling of a flat plate at M = 2.7 with air as the injected gas

Description: Report presenting local values of heat-transfer rate and temperature-recovery factor obtained on a transpiration-cooled flat plate. The results show primarily that transpiration cooling in a turbulent boundary layer at M = 2.7 has marked effects on the heat transfer and recovery temperature for nearly uniform air injection along the plate.
Date: December 21, 1955
Creator: Rubesin, Morris W.; Pappas, Constantine C. & Okuno, Arthur F.
Item Type: Refine your search to only Report
open access

Effect of outer-shell design on performance characteristics of convergent-plug exhaust nozzles

Description: Report presenting an investigation to determine the effect of outer-shell design variables on the internal performance characteristics of plug-type nozzles designed for a pressure ratio between 6 and 12. Inlet Mach number and outer-shell angle were found to have no effect on nozzle thrust coefficient. For choked flow, the effective throat area decreased when the inlet Mach number or outer-shell angle was increased.
Date: April 21, 1955
Creator: Krull, H. George & Beale, William T.
Item Type: Refine your search to only Report
open access

An experimental investigation at a Mach number of 2.01 of the effects of body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies of a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. The results showed that changes in drag at zero lift due to changes in body cross-section shape from the basic circular shape are small and of the same order a… more
Date: July 21, 1955
Creator: Carlson, Harry W. & Gapcynski, John P.
Item Type: Refine your search to only Report
open access

Experimental studies of flutter of buckled rectangular panels at Mach numbers from 1.2 to 3.0 including effects of pressure differential and of panel width-length ratio

Description: Report presenting experimental panel flutter data at a range of Mach numbers for buckled rectangular panels and the effect of a pressure differential. Increasing the pressure differential was found to eliminate flutter on most of the panels tested. Results regarding buckled panels clamped on the front and rear edges, bucked panels clamped on four edges, effect of lengthwise stiffeners on the flutter of a buckled panel, and panel flutter stresses are provided.
Date: December 21, 1955
Creator: Sylvester, Maurice A.
Item Type: Refine your search to only Report
open access

Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees

Description: A flight investigation was made at altitudes of 40,000, 25,000 and 15,000 feet to determine the horizontal-tail loads of the Bell X-5 research airplane at a sweep angle of 58.7 deg over the lift range of the airplane for Mach numbers from 0.61 to 1.00. The horizontal-tail loads were found to be nonlinear with lift throughout the lift ranges tested at all Mach numbers except at a Mach number of 1.00. The balancing tail loads reflected the changes which occur in the wing characteristics with inc… more
Date: July 21, 1955
Creator: Reed, Robert D.
Item Type: Refine your search to only Report
open access

Flux distribution in uranium slug in the presence of a boron carbide spline

Description: A potentially attractive method of achieving additional flexible reactivity control in the production reactors is that of introducing neutron absorbers contained in thin flexible metal strips between the slug and process tube wall. It is possible that the neutron absorbing splines could be used to provide additional flexible control during operation as well as temporary control during outages. The application of splines during reactor operation is contingent upon the neutron absorber creating t… more
Date: September 21, 1955
Creator: Simpson, D. E. & Niemuth, W. E.
Item Type: Refine your search to only Report
open access

Hanford Atomic Products Operation monthly report, January 1955

Description: This document presents a summary of work and progress at the Hanford Engineer Works for January 1955. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical Design, and Project Section… more
Date: February 21, 1955
Item Type: Refine your search to only Report
open access

High-Speed Cascade Tests of the NACA 65-(12A(sub 10))10 and NACA 65-(12A(sub 2)I(sub 8b))10 Compressor Blade Sections

Description: "Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade sections were made at Mach numbers from 0.3 to choking in most cases. Data were obtained at solidities of 1.0 and 1.5 at inlet-air angles of 45 deg. and 60 deg. for both blade sections. With a solid--wall modification to the cascade tunnel, schlieren observations were made of the flow in cascade at a solidity of 1.5 and inlet-air angle of 45 deg. and at a solidity of 1.0 and inlet-air angle of 60… more
Date: December 21, 1955
Creator: Dunavant, James C.; Emery, James C.; Walch, Howard C. & Westphal, Willard R.
Item Type: Refine your search to only Report
open access

An Integrated Miniature Solvent Extraction System for Processing Radioactive Solutions

Description: Abstract: "Because of the radiation hazards inherent in processing large volumes of radioactive solutions by solvent extraction techniques, there is need for a system with small hold-up which can be contained within a minimum of shielding and yet which is versatile enough to be used as a research tool. A system utilizing a miniature mixer-settler has been constructed and its successful operation by remote means demonstrated. The unit is semiportable and employs a number of novel features of val… more
Date: June 21, 1955
Creator: Bloom, Justin L.
Item Type: Refine your search to only Report
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