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Partner:
UNT Libraries Government Documents Department
Decade:
1950-1959
Year:
1953
Month:
November
Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range
Date: November 2, 1953
Creator: Hatch, John E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59872/
Aerodynamic characteristics of low-aspect-ratio wings at high supersonic Mach numbers
Date: November 2, 1953
Creator: Ulmann, Edward F
Description: This paper presents some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach numbers of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. Data on lifting wings in the Mach number range above 2.5 are not plentiful and most of the available data may be found in NACA RM L51D17, NACA RM L51D30, NACA RM L52D15a, NACA RM L52K19, NACA RM L53D03, and NACA RM L53D30a.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62745/
Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers
Date: November 2, 1953
Creator: Bertram, M. H.
Description: Aerodynamic characteristics of low-aspect-ratio wings at supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc52946/
An analytical investigation of the effect of the rate of increase of turbulent kinetic energy in the stream direction on the development of turbulent boundary layers in adverse pressure gradients
Date: November 1, 1953
Creator: Rashis, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56754/
Application of silver chloride in investigations of elasto-plastic states of stress
Date: November 1, 1953
Creator: Goodman, L E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56728/
Applications of auxiliary air injectors to supersonic wind tunnels
Date: November 25, 1953
Creator: Spiegel, Joseph M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc60515/
Drag measurements at low lift of a four-nacelle airplane configuration having a longitudinal distribution of cross-sectional area conducive to low transonic drag rise
Date: November 18, 1953
Creator: Hopko, Russell N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59678/
Drag measurements at low lift of a four- nacelle airplane configuration having a longitudinal distribution of cross-sectional area conductive to low transonic drag rise
Date: November 18, 1953
Creator: Hall, J. R.
Description: Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc52974/
Effect of a Rapid Blade-Pitch Increase on the Thrust and Induced-Velocity Response of a Full-Scale Helicopter Rotor
Date: November 1, 1953
Creator: Carpenter, Paul J
Description: A method has been proposed for predicting the effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a helicopter rotor. General equations have been derived for the ensuing motion of the helicopter. These equations yield time histories of thrust, induced velocity, and helicopter vertical velocity for given rates of blade-pitch-angle changes and given rotor-angular-velocity time histories. The results of the method have been compared with experimental results obtained with a rotor mounted on the Langley helicopter test tower. The calculated and experimental results are in good agreement, although, in general, the calculated thrust-coefficient overshoots are about 10 percent greater than those obtained experimentally.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56734/
The effect of vertical chine strips on the planing characteristics of V- shaped prismatic surfaces having angles of dead rise of 20 degrees and 40 degrees
Date: November 1, 1953
Creator: Kapryan, Walter J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56762/