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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Date: May 7, 1957
Creator: Slone, Henry O & Donoughe, Patrick L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Gas-to-blade heat-transfer coefficients and turbine heat-rejection rates for a range of one-spool cooled-turbine engine designs

Gas-to-blade heat-transfer coefficients and turbine heat-rejection rates for a range of one-spool cooled-turbine engine designs

Date: May 14, 1956
Creator: Slone, Henry O & Esgar, Jack B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines IV : coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades

Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines IV : coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades

Date: May 11, 1955
Creator: Slone, Henry O & Hubbartt, James E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine rotor blade temperatures in a turbojet engine operating at turbine-inlet temperatures up to 2580 R and altitudes of 50,000 and 60,000 feet

Experimental investigation of air-cooled turbine rotor blade temperatures in a turbojet engine operating at turbine-inlet temperatures up to 2580 R and altitudes of 50,000 and 60,000 feet

Date: August 20, 1956
Creator: Slone, Henry O; Cochran, Reeves P & Dengler, Robert P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Method of designing corrugated surfaces having maximum cooling effectiveness within pressure-drop limitations for application to cooled turbine blades

Method of designing corrugated surfaces having maximum cooling effectiveness within pressure-drop limitations for application to cooled turbine blades

Date: December 9, 1954
Creator: Slone, Henry O; Hubbartt, James E & Arne, Vernon L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Internal-Film Cooling of Rocket Nozzles

Internal-Film Cooling of Rocket Nozzles

Date: June 8, 1948
Creator: Sloop, J L & Kinney, George R
Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections.
Contributing Partner: UNT Libraries Government Documents Department
Temperature survey of the wake of two closely located parallel jets

Temperature survey of the wake of two closely located parallel jets

Date: February 6, 1950
Creator: Sloop, John L & Morrell, Gerald
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Date: September 13, 1957
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of internal coolants on knock-limited and temperature-limited power as determined in a single-cylinder aircraft test engine

Some effects of internal coolants on knock-limited and temperature-limited power as determined in a single-cylinder aircraft test engine

Date: August 1, 1944
Creator: Slough, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Supercharged-engine knock tests of methyl tert-butyl ether

Supercharged-engine knock tests of methyl tert-butyl ether

Date: August 1, 1944
Creator: Slough, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Interim Report: Faret Experimental Program

Interim Report: Faret Experimental Program

Date: April 1963
Creator: Smaardyk, A.; Bump, T. R.; Handwerk, J. & Handwerk, J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
EBR-II Environmental Instrumented Subassembly XX08 : Engineering and Assembly

EBR-II Environmental Instrumented Subassembly XX08 : Engineering and Assembly

Date: May 1978
Creator: Smaardyk, A.; Filewicz, E. C.; Longnecker, A. A.; Poloncsik, J.; Tokar, J. V.; Walker, D. E. et al.
Description: Subassembly XX08 is a fueled and instrumented subassembly designed primarily for an ongoing program to investigate the thermal-hydraulic core environment within EBR-II under normal and off-normal plant operating conditions. XX08 contains 58-xenon-tagged, EBR-II Mark-II driver-fuel elements. The Mark-II fuel is expected to provide XX08 with an irradiation lifetime three times as great as that attained with its predecessor, XX07, i.e., a 9 versus 2.9% burnup. A burnup of 9 at.% is equivalent to about 29,000 MWt dyays of EBR-II reactor operation, which corresponds to 11 reactor runs at 2700 MWd per run.
Contributing Partner: UNT Libraries Government Documents Department
Practical methods of calculation involved in the experimental study of an autopilot and the autopilot-aircraft combination

Practical methods of calculation involved in the experimental study of an autopilot and the autopilot-aircraft combination

Date: June 1, 1951
Creator: Smaus, Louis H & Stewart, Elwood C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Dynamic Response of Control Servo System Installed in NAES-Equipped SB2C-5 Airplane (BuAer No. 83135)

Dynamic Response of Control Servo System Installed in NAES-Equipped SB2C-5 Airplane (BuAer No. 83135)

Date: October 5, 1950
Creator: Smaus, Louis H. & Stewart, Elwood C.
Description: Dynamic--response measurements for various conditions of displacement and rate signal input, sensitivity setting, and simulated hinge moment were made of the three control-surface servo systems of an NAES-equipped remote-controlled airplane while on the ground. The basic components of the servo systems are those of the General Electric Company type G-1 autopilot using electrical signal. sources, solenoid-operated valves, and hydraulic pistons. The test procedures and difficulties are discussed, Both frequency and transient-response data, are presented and comparisons are made. The constants describing the servo system, the undamped natural frequency, and the damping ratio, are determined by several methods. The response of the system with the addition of airframe rate signal is calculated. The transfer function of the elevator surface, linkage, and cable system is obtained. The agreement between various methods of measurement and calculation is considered very good. The data are complete enough and in such form that they may be used directly with the frequency-response data of an airplane to predict the stability of the autopilot-airplane combination.
Contributing Partner: UNT Libraries Government Documents Department
A comparison of predicted and experimentally determined longitudinal dynamic responses of a stabilized airplane

A comparison of predicted and experimentally determined longitudinal dynamic responses of a stabilized airplane

Date: December 1, 1951
Creator: Smaus, Louis, H; Gore, Marvin R & Waugh, Merle G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of Automation of Message Handling Functions at USCG COMSTA/RADSTA and Communication Centers

Study of Automation of Message Handling Functions at USCG COMSTA/RADSTA and Communication Centers

Date: May 1978
Creator: Smiley, D.; Keene, G. & Kennedy, P.
Description: Abstract: This study examines current Coast Guard message handling functions to (1) confirm the need for the application of communications automation techniques to such operations and (2) develop alternative approaches to accomplishing such automation.
Contributing Partner: UNT Libraries Government Documents Department
The application of planing characteristics to the calculation of the water-landing loads and motions of seaplanes of arbitrary constant cross section

The application of planing characteristics to the calculation of the water-landing loads and motions of seaplanes of arbitrary constant cross section

Date: November 1, 1952
Creator: Smiley, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation, evaluation, and extension of linearized theories for tire motion and wheel shimmy

Correlation, evaluation, and extension of linearized theories for tire motion and wheel shimmy

Date: January 1, 1957
Creator: Smiley, Robert F
Description: An evaluation is made of the existing theories of a linearized tire motion and wheel shimmy. It is demonstrated that most of the previously published theories represent varying degrees of approximation to a summary theory developed in this report which is a minor modification of the basic theory of Von Schlippe and Dietrich. In most cases where strong differences exist between the previously published theories and summary theory, the previously published theories are shown to possess certain deficiencies. A series of systematic approximations to the summary theory is developed for the treatment of problems too simple to merit the use of the complete summary theory, and procedures are discussed for applying the summary theory and its systematic approximations to the shimmy of more complex landing-gear structures than have previously been considered. Comparisons of the existing experimental data with the predictions of the summary theory and the systematic approximations provide a fair substantiation of the more detailed approximate theories.
Contributing Partner: UNT Libraries Government Documents Department
Correlation, evaluation, and extension of linearized theories for tire motion and wheel shimmy

Correlation, evaluation, and extension of linearized theories for tire motion and wheel shimmy

Date: June 1, 1956
Creator: Smiley, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An experimental study of water-pressure distributions during landings and planing of a heavily loaded rectangular flat-plate model

An experimental study of water-pressure distributions during landings and planing of a heavily loaded rectangular flat-plate model

Date: September 1, 1951
Creator: Smiley, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A semiempirical procedure for computing the water-pressure distribution on flat and v-bottom prismatic surfaces during impact or planing

A semiempirical procedure for computing the water-pressure distribution on flat and v-bottom prismatic surfaces during impact or planing

Date: December 1, 1951
Creator: Smiley, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some considerations of hysteresis effects on tire motion and wheel shimmy

Some considerations of hysteresis effects on tire motion and wheel shimmy

Date: June 1, 1957
Creator: Smiley, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of water pressure distribution during landings with special reference to a prismatic model having a heavy beam loading and a 30 degree angle of dead rise

A study of water pressure distribution during landings with special reference to a prismatic model having a heavy beam loading and a 30 degree angle of dead rise

Date: July 1, 1950
Creator: Smiley, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical and experimental investigation of the effects of yaw on pressures, forces, and moments during seaplane landings and planing

A theoretical and experimental investigation of the effects of yaw on pressures, forces, and moments during seaplane landings and planing

Date: November 1, 1952
Creator: Smiley, Robert F
Description: A theory for the side force, rolling moment, yawing moment, and pressure distribution during yawed landings and planing of seaplanes was developed. For the special case of the straight-sided wedge without chine immersion, the results of the theoretical analysis are presented in the form of generalized curves covering all step landing conditions. Experimental impact and planing data are presented for a prismatic wedge having an angle of dead rise of 22.5 degrees and are shown to be in reasonable agreement with the theoretical predictions.
Contributing Partner: UNT Libraries Government Documents Department