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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: Technical Report Archive and Image Library
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 0 and -3 degree trim and with a 22 1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 0 and -3 degree trim and with a 22 1/2 degree angle of dead rise

Date: April 1, 1947
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise

Date: February 1, 1945
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 6 degrees and 9 degrees trim and a 22-1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 6 degrees and 9 degrees trim and a 22-1/2 degree angle of dead rise

Date: February 1, 1946
Creator: Stewart, Thelma
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise

Date: February 1, 1946
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility

Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility

Date: October 1, 1944
Creator: Cleary, Harold E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of properties throughout cross section of two extruded shapes

Variation of properties throughout cross section of two extruded shapes

Date: September 1, 1941
Creator: Howell, F M
Description: Tensile and compressive properties were determined of specimens cut from the fins and the main bodies of two different extruded shapes of 24S-T aluminum alloy. The specimens from the fins as compared with those from the main body of the section showed: tensile strengths from 5000 to 10,000 pounds per square inch lower; tensile yield strengths and compressive yield strengths 4000 to 9000 pounds per square inch lower. The compressive yield strength values for any given location in the cross sections were about 1000 to 6000 pounds per square inch lower than the tensile strength values for the same location.
Contributing Partner: UNT Libraries Government Documents Department
Variation with Mach Number of Static and Total Pressures Through Various Screens

Variation with Mach Number of Static and Total Pressures Through Various Screens

Date: February 1, 1946
Creator: Adler, Alfred A
Description: Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire dimmeter for an installation so that the choking Mach number is.
Contributing Partner: UNT Libraries Government Documents Department
Variations in Oxygen Condition Between Individual Cartridges and Between Cases of Permissible Explosives

Variations in Oxygen Condition Between Individual Cartridges and Between Cases of Permissible Explosives

Date: June 1942
Creator: Rowles, A. P. & Denues, A. R. T.
Description: Report issued by the U.S. Bureau of Mines on the differing conditions of oxygen in explosives. Results from explosives samples with oxygen variations are presented. This report includes tables.
Contributing Partner: UNT Libraries Government Documents Department
Velocity distribution on wing sections of arbitrary shape in compressible potential flow I : symmetric flows obeying the simplified density-speed relation

Velocity distribution on wing sections of arbitrary shape in compressible potential flow I : symmetric flows obeying the simplified density-speed relation

Date: April 1, 1946
Creator: Bers, Lipman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Velocity distribution on wing sections of arbitrary shape in compressible potential flow II : subsonic symmetric adiabatic flows

Velocity distribution on wing sections of arbitrary shape in compressible potential flow II : subsonic symmetric adiabatic flows

Date: June 1, 1946
Creator: Bers, Lipman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Velocity distributions on two-dimensional wing-duct inlets by conformal mapping

Velocity distributions on two-dimensional wing-duct inlets by conformal mapping

Date: January 1, 1948
Creator: Perl, W & Moses, H E
Description: The conformal-mapping method of the Cartesian mapping function is applied to the determination of the velocity distribution on arbitrary two-dimensional duct-inlet shapes such as are used in wing installations. An idealized form of the actual wing-duct inlet is analyzed. The effects of leading edge stagger, inlet-velocity ratio, and section lift coefficients on the velocity distribution are included in the analysis. Numerical examples are given and, in part, compared with experimental data.
Contributing Partner: UNT Libraries Government Documents Department
Velocity gained and altitude lost in recoveries from inclined flight paths

Velocity gained and altitude lost in recoveries from inclined flight paths

Date: October 1, 1941
Creator: Pearson, H A & Garvin, J B
Description: A series of charts is given showing the variation of the velocity gained and the altitude lost in dive pullouts with the initial indicated air speed and the dive angle. The effects of the maximum load factor, the drag parameter K, the initial altitude, and the type of recovery on the velocity gained and the altitude lost are also considered. The results were obtained from a step-by-step solution of the equations of motion in which mean values of the air density and the airplane drag coefficient were used. The load-factor variation with time is arbitrarily specified in various ways to simulate pull-out procedures, some of which might be encountered in flight.
Contributing Partner: UNT Libraries Government Documents Department
Venturi Tube with Varying Mass Flow

Venturi Tube with Varying Mass Flow

Date: March 1, 1948
Creator: Regenscheit, B.
Description: Measurements on three tubes with flow regulated by suction at the trainling edge of the tube are described. It was possible to vary the mass of air flowing through the tube over a large range. Such tubes could be used for shrouded propellers.
Contributing Partner: UNT Libraries Government Documents Department
Vibration of loosely mounted turbine blades during service operation of a turbojet engine with centrifugal compressor and straight-flow combustion chambers

Vibration of loosely mounted turbine blades during service operation of a turbojet engine with centrifugal compressor and straight-flow combustion chambers

Date: November 3, 1949
Creator: Morgan, W C; Kemp, R H & Manson, S S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration of turbine blades in a turbojet engine during operation

Vibration of turbine blades in a turbojet engine during operation

Date: April 22, 1948
Creator: Morgan, W C; Kemp, R H & Manson, S S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration-response tests of a 1/5-scale model of the Grumman F6F airplane in the Langley 16-foot high-speed tunnel

Vibration-response tests of a 1/5-scale model of the Grumman F6F airplane in the Langley 16-foot high-speed tunnel

Date: November 1, 1944
Creator: Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration survey of blades in 10-stage axial-flow compressor I : static investigation

Vibration survey of blades in 10-stage axial-flow compressor I : static investigation

Date: January 31, 1949
Creator: Meyer, Andre J , Jr & Calvert, Howard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration Survey of Blades in 19XB Axial-Flow Compressor, 2, Dynamic Investigation

Vibration Survey of Blades in 19XB Axial-Flow Compressor, 2, Dynamic Investigation

Date: April 9, 1947
Creator: Meyer, Andre J., Jr. & Calvert, Howard F.
Description: Strain-gage measurements were taken under operating conditions from blades of various stages of the 19XB axial-flow compressor in an effort to determine the reason for failures in the seventh and tenth stages. First bending-mode vibrations were detected in the first five stages of the compressor caused by each integral multiple of rotor speed from three through ten. Lead-wire failures in the last five stages resulted in incomplete data. The dynamic-vibration frequencies at various rotor speeds were compared with statically measured frequencies analytically corrected for the influence of centrifugal force. Large increases in vibration ani~litude with increased pressure ratio were observed. During surging operation, blade vibrations were not present. The effects of pressure ratio and surge indicate the existence of aerodynamic excitation as the cause of the blade vibrations.
Contributing Partner: UNT Libraries Government Documents Department
Vibration Survey of Blades in 19XB Axial-Flow Compressor, 3, Preliminary Engine Investigation

Vibration Survey of Blades in 19XB Axial-Flow Compressor, 3, Preliminary Engine Investigation

Date: January 28, 1948
Creator: Meyer, Andre J., Jr. & Calvert, Howard F.
Description: Strain gages were used to measure blade vibrations possibly causing failure in the 10-stage compressor of the 19XB jet-propulsion engine. The seventh and tenth stages were of great concern as a result of failures experienced by the manufacturer. Strain-gage records were obtained from all stages during acceleration, deceleration, and constant speed runs. Curves are presented herein showing the maximum allowable vibratory stress for a given speed, the change of the damping coefficient with the mounting of a strain gage at the base of the blade, the effect of rotor speed, on blade natural frequency, and the effect of the order of first bending-mode vibration on stress. It was found that for all stages the lower the order of vibration the higher the stress but no destructive vibrations were detected.
Contributing Partner: UNT Libraries Government Documents Department
Vibration survey of NACA 24-inch supersonic axial-flow compressor

Vibration survey of NACA 24-inch supersonic axial-flow compressor

Date: July 30, 1948
Creator: Meyer, Andre J , Jr & Hanson, Morgan P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration surveys of the P-40 rudder and fin-rudder assembly

Vibration surveys of the P-40 rudder and fin-rudder assembly

Date: January 1, 1943
Creator: Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration surveys of the P-47-B rudder and fin-rudder assembly

Vibration surveys of the P-47-B rudder and fin-rudder assembly

Date: April 1, 1943
Creator: Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibrational modes of several hollow turbine blades and of solid turbine blade of similar aerodynamic design

Vibrational modes of several hollow turbine blades and of solid turbine blade of similar aerodynamic design

Date: October 3, 1949
Creator: Kemp, R H & Shifman, J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Video Amplifier & Scope

Video Amplifier & Scope

Date: 1945
Creator: Titterton, E. W.
Description: Technical drawing of video amplifiers for nuclear reactors.
Contributing Partner: UNT Libraries Government Documents Department