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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Month: March
 Collection: Technical Report Archive and Image Library
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 3, Performance and Windmilling Drag Characteristics

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 3, Performance and Windmilling Drag Characteristics

Date: March 13, 1957
Creator: Fleming, WIlliam A. & Dietz, Robert O., Jr.
Description: The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions. Data for these two engines are presented to show the effect of altitude, free-stream ram-pressure ratio, and tail-pipe-nozzle area on engine performance. A 21-percent reduction in tail-pipe-nozzle area of the 19B-8 engine increased the let thrust 43 percent the net thrust 72 percent, and the fuel consumption 64 percent. An increase in free-stream ram-pressure ratio raised the jet thrust and the air flow and lowered the net thrust throughout the entire range of engine speeds for the 19B-8 engine. At similar operating conditions, the corrected jet thrust and corrected air flow were approximately the same for both engines, and the corrected specific fuel consumption based on jet thrust was lower for the 19XB-1 engine than for the 19B-8 engine. The thrust and air-flow data obtained with both engines at various altitudes for a given free-stream ...
Contributing Partner: UNT Libraries Government Documents Department
Analysis of experimental low-speed loss and stall characteristics of two-dimensional compressor blade cascades

Analysis of experimental low-speed loss and stall characteristics of two-dimensional compressor blade cascades

Date: March 19, 1957
Creator: Lieblein, Seymour
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Brief studies of turbojet combustor and fuel-system operation with hydrogen fuel at -400 deg f

Brief studies of turbojet combustor and fuel-system operation with hydrogen fuel at -400 deg f

Date: March 7, 1957
Creator: Christenson, H. H.; Smith, A. L. & Straight, D. M.
Description: Turbojet combustor and fuel system operation with hydrogen fuel at -400 deg F.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers up to 1.9

Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers up to 1.9

Date: March 27, 1957
Creator: Petersen, R. B.
Description: Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions. The agreement between theoretical and experimental zero-lift wave-drag coefficients was generally very good, especially for a fuselage or for fuselage-wing combinations that were vertically symmetrical. For other models that had rapid changes in body shape and/or were not vertically symmetrical, the agreement of theory with experiment ranged from fair to poor, depending on the severity of the change in shape.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade

Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade

Date: March 1, 1957
Creator: Westphal, Willard R & Godwin, William R
Description: An investigation has been conducted to compare the performance of NACA 65-series compressor blades in two-dimensional cascade with that in an axial flow compressor. Blade pressure distributions were obtained by the use of a mercury-seal pressure-transfer device. The comparison indicated that cascade data accurately predicted the turning angle and blade pressure distribution obtained in the compressor at design conditions.
Contributing Partner: UNT Libraries Government Documents Department
A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed

A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed

Date: March 1, 1957
Creator: Felix, A Richard & Emery, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Conceptual Design of an Advanced Engineering Test Reactor

Conceptual Design of an Advanced Engineering Test Reactor

Date: March 1, 1957
Creator: Mallon, R. G.; Saldick, J. & Gibbons, R. E.
Description: From abstract: This report describes a conceptual design for an Advanced Engineering Test Reactor. The reactor is a large graphite assembly penetrated by parallel Zircaloy tubes through which flow as heavy water solution of uranyl sulfate. Reactor power is 220 megawatts.
Contributing Partner: UNT Libraries Government Documents Department
A correlation of low-speed, airfoil-section stalling characteristics with Reynolds number and airfoil geometry

A correlation of low-speed, airfoil-section stalling characteristics with Reynolds number and airfoil geometry

Date: March 1, 1957
Creator: Gault, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and investigation of a transonic axial-flow compressor rotor with an inlet hub-tip radius ratio of essentially zero

Design and investigation of a transonic axial-flow compressor rotor with an inlet hub-tip radius ratio of essentially zero

Date: March 11, 1957
Creator: Westphal, Willard R & Maynard, John W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effects of Irradiation Cycling on Pressurized Water Reactor Blanket Fuel Elements

The Effects of Irradiation Cycling on Pressurized Water Reactor Blanket Fuel Elements

Date: March 13, 1957
Creator: Eichenberg, John D.
Description: ...
Contributing Partner: UNT Libraries Government Documents Department
Engineering, Construction and Cost of the Argonaut Reactor

Engineering, Construction and Cost of the Argonaut Reactor

Date: March 1957
Creator: Armstrong, R. H.; Kolb, W. L.; Lennox, D. H.; Kelber, C. N.; Selep, Andrew & Spinrad, B. I.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The erosion of meteors and high-speed vehicles in the upper atmosphere

The erosion of meteors and high-speed vehicles in the upper atmosphere

Date: March 1, 1957
Creator: Hansen, C Frederick
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental comparison of speed : fuel-flow and speed-area controls on a turbojet engine for small step disturbances

Experimental comparison of speed : fuel-flow and speed-area controls on a turbojet engine for small step disturbances

Date: March 1, 1957
Creator: Wenzel, L M; Hart, C E & Craig, R T
Description: Optimum proportional-plus-integral control settings for speed - fuel-flow control, determined by minimization of integral criteria, correlated well with analytically predicted optimum settings. Engine response data are given for a range of control settings around the optimum. An inherent nonlinearity in the speed-area loop necessitated the use of nonlinear controls. Response data for two such nonlinear control schemes are presented.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of temperature feedback control systems applicable to turbojet-engine control

Experimental investigation of temperature feedback control systems applicable to turbojet-engine control

Date: March 1, 1957
Creator: Hart, C E; Wenzel, L M & Craig, R T
Description: Temperature - fuel-flow and temperature-area feedback control systems were investigated as means of controlling tailpipe gas temperature of a turbojet engine during transient operation in the high-speed region. Proportional-plus-integral control was used in both systems, but in the temperature-area control system it was necessary to add nonlinear components to the basic proportional-plus-integral control to provide satisfactory transient response to a desired step increase in temperature. Time integral of temperature-error functions were used as criteria for determining optimum transient response. A description of engine dynamics was obtained from frequency-response data.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the forces and moments due to sideslip of a series of triangular vertical- and horizontal-tail combinations at Mach numbers of 1.62, 1.93, and 2.41

Experimental investigation of the forces and moments due to sideslip of a series of triangular vertical- and horizontal-tail combinations at Mach numbers of 1.62, 1.93, and 2.41

Date: March 1, 1957
Creator: Coletti, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler

Experimental investigation of the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler

Date: March 1, 1957
Creator: Clevenson, Sherman A & Tomassoni, John E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from unswept-, sweptback and modified-delta-wing-fuselage combinations at zero sideslip

Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from unswept-, sweptback and modified-delta-wing-fuselage combinations at zero sideslip

Date: March 19, 1957
Creator: Alford, William J & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight-determined static lateral stability and control characteristics of a swept-wing fighter airplane to a Mach number of 1.39

Flight-determined static lateral stability and control characteristics of a swept-wing fighter airplane to a Mach number of 1.39

Date: March 11, 1957
Creator: Matranga, Gene J & Peele, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation and theoretical calculations of the fuselage deformations of a swept-wing bomber during push-pull maneuvers

Flight investigation and theoretical calculations of the fuselage deformations of a swept-wing bomber during push-pull maneuvers

Date: March 29, 1957
Creator: Mayo, Alton, P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of a model of a high-wing transport vertical-take-off airplane with tilting wing and propellers and with jet controls at the rear of the fuselage for pitch and yaw control

Flight tests of a model of a high-wing transport vertical-take-off airplane with tilting wing and propellers and with jet controls at the rear of the fuselage for pitch and yaw control

Date: March 1, 1957
Creator: Lovell, Powell M , Jr & Parlett, Lysle P
Description: An investigation of the stability and control of a high-wing transport vertical-take-off airplane with four engines during constant-altitude transitions from hovering to normal forward flight was conducted with a remotely controlled free-flight model. The model had four propellers distributed along the wing with the thrust axes in the wing chord plane. The wing could be rotated to 90 degrees incidence so that the propeller thrust axes were vertical for hovering flight. An air jet at the rear of the fuselage provided pitch and yaw control for hovering and low-speed flight.
Contributing Partner: UNT Libraries Government Documents Department
The influence of imperfect radar space stabilization on the final attack phase of an automatic interceptor system

The influence of imperfect radar space stabilization on the final attack phase of an automatic interceptor system

Date: March 11, 1957
Creator: Triplett, William C; Mclean, John D & White, John S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation at low speed of the flow over a simulated flat plate at small angles of attack using pitot-static and hot-wire probes

An investigation at low speed of the flow over a simulated flat plate at small angles of attack using pitot-static and hot-wire probes

Date: March 1, 1957
Creator: Gault, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of a high-performance top inlet to Mach number of 2.0 and at angles of attack to 20 degrees

Investigation of a high-performance top inlet to Mach number of 2.0 and at angles of attack to 20 degrees

Date: March 20, 1957
Creator: Vargo, Donald J; Parks, Philip N & Davis, Owen H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of an underslung normal-wedge inlet at free-stream mach numbers from 1.50 to 1.99

Investigation of an underslung normal-wedge inlet at free-stream mach numbers from 1.50 to 1.99

Date: March 19, 1957
Creator: Vargo, D. J. & Weinstein, M. I.
Description: Wedge and scoop air inlet performance and thrust minus drag comparisons at free stream in supersonic wind tunnel test.
Contributing Partner: UNT Libraries Government Documents Department
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