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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Date: April 17, 1957
Creator: Branstetter, J Robert
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.
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
Altitude starting tests of a small solid propellant rocket

Altitude starting tests of a small solid propellant rocket

Date: June 21, 1957
Creator: Krawczoner, E. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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.
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
American Standard Recommended Practice for Drainage of Coal Mines (M6.1-1955, UDC 622.5)

American Standard Recommended Practice for Drainage of Coal Mines (M6.1-1955, UDC 622.5)

Date: 1957
Creator: United States. Bureau of Mines.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability

An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability

Date: February 19, 1957
Creator: Creer, Brent Y
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analog computer study of some filtering, command-computer, and automatic-pilot problems connected with the attack phase of the automatically controlled supersonic interceptor

Analog computer study of some filtering, command-computer, and automatic-pilot problems connected with the attack phase of the automatically controlled supersonic interceptor

Date: October 3, 1957
Creator: Sherman, Windsor L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Date: June 18, 1957
Creator: Morris, James F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Date: June 18, 1957
Creator: Morris, J. F.
Description: Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine.
Contributing Partner: UNT Libraries Government Documents Department
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
Description: None
Contributing Partner: UNT Libraries Government Documents Department