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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
Aerodynamic interference of slender wing-tail combinations

Aerodynamic interference of slender wing-tail combinations

Date: January 1957
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Date: December 5, 1957
Creator: West, F E , Jr; Whitcomb, Charles F & Schmeer, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Date: July 23, 1957
Creator: Polhamus, E. C. & Spahr, J. R.
Description: Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory. A relatively simple, but general, theoretical method for calculating these load and moment characteristics is described, and the results from this method are found to be in good agreement with experiment provided the initial positions of the forebody vortices are known. It is shown that a simple application of slender-body theory can be used to predict the side loads due to sideslip that are contributed by a vertical tail on a wide variety of wing-body-tail combinations at low angles of attack. For several configurations, changes are indicated which reduced the vertical-tail loads per unit yawing moment of each complete configuration at large angles of attack. Some results are presented on the effect of high angle of attack on the induced-flow field and tail loads due to a wing at supersonic ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance of several techniques for spike-position control of  a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0

Aerodynamic performance of several techniques for spike-position control of a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0

Date: September 17, 1957
Creator: Anderson, Arthur A & Weinstein, Maynard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Date: June 17, 1957
Creator: Clevenson, S. A. & Thompson, R. F.
Description: Aerodynamic forces and moments of oscillating control surfaces at transonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Aging Characteristics of Hastelloy B

Aging Characteristics of Hastelloy B

Date: August 12, 1957
Creator: Clausing, Robert E.; Patriarca, P. & Manly, W. D.
Description: Report issued by the Oak Ridge National Laboratory discussing the aging characteristics of the alloy Hastelloy B. Materials, equipment, experimental procedures, and results used to determine the characteristics of the alloy are presented. This report includes tables, illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
An air-borne target simulator for use with scope-presentation type fire-control systems

An air-borne target simulator for use with scope-presentation type fire-control systems

Date: May 10, 1957
Creator: Foster, John V; Fulcher, Elmer C & Heinle, Donovan R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airborne Radiometric Reconnaissance in the Wind River Basin, Wyoming

Airborne Radiometric Reconnaissance in the Wind River Basin, Wyoming

Date: June 1957
Creator: Loomis, Tom H. W. & Blair, Robert G.
Description: Abstract: A program of airborne radiometric reconnaissance for uranium was conducted in eastern Fremont and western Natrona Counties, in central Wyoming, during the summer and fall of 1954, by the U.S. Atomic Energy Commission.
Contributing Partner: UNT Libraries Government Documents Department
Airplane measurements of atmospheric turbulence for altitudes between 20,000 and 55,000 feet over the western part of the United States

Airplane measurements of atmospheric turbulence for altitudes between 20,000 and 55,000 feet over the western part of the United States

Date: August 23, 1957
Creator: Coleman, Thomas L & Coe, Emilie C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Date: August 19, 1957
Creator: Algranti, J. S.; Braithwaite, W. M. & Fenn, D. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude free-jet investigation of dynamics of a 28-inch-diameter ram-jet engine

Altitude free-jet investigation of dynamics of a 28-inch-diameter ram-jet engine

Date: January 15, 1957
Creator: Crowl, R. J.; Dunbar, W. R. & Wentworth, C. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a full-scale turbojet engine using pentaborane fuels

Altitude performance of a full-scale turbojet engine using pentaborane fuels

Date: February 28, 1957
Creator: Useller, James W; Kaufman, Warner B & Jones, William L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a turbojet engine using pentaborane fuel

Altitude performance of a turbojet engine using pentaborane fuel

Date: May 20, 1957
Creator: Sivo, Joseph N
Description: A full-scale turbojet engine having a two-stage turbine was operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. The specific fuel consumption was initially reduced 32 percent below that obtained with gasoline fuel; however, the occurrence of a 25-percent reduction in net thrust after 8 minutes of operation resulted in a subsequent increase in specific fuel consumption to a value only 11.5 percent lower than that for gasoline.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a turbojet engine using pentaborane fuel

Altitude performance of a turbojet engine using pentaborane fuel

Date: May 20, 1957
Creator: Sivo, J. N.
Description: Altitude performance of turbojet engine using pentaborane fuel.
Contributing Partner: UNT Libraries Government Documents Department
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 & Kaufman, Warner B
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
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. & Sloop, J. L.
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. & 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
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: unknown
Description: Report discussing standardizations when dealing with pumps for draining and storing water in coal mines.
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 & Donoughe, Patrick L
Description: None
Contributing Partner: UNT Libraries Government Documents Department