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 Decade: 1940-1949
 Year: 1949
 Collection: National Advisory Committee for Aeronautics Collection
The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

Date: January 7, 1949
Creator: Weinflash, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Date: January 12, 1949
Creator: Lockwood, Vernard E; Vogler, Raymond D & Turner, Thomas R
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
Langley free-flight-tunnel investigation of the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that provided either flicker-type or hunting control

Langley free-flight-tunnel investigation of the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that provided either flicker-type or hunting control

Date: January 11, 1949
Creator: Schade, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Stability results obtained with Douglas D-558-1 airplane (BuAero No. 37971) in flight up to a Mach number of 0.89

Stability results obtained with Douglas D-558-1 airplane (BuAero No. 37971) in flight up to a Mach number of 0.89

Date: April 22, 1949
Creator: Lilly, Howard C & Barlow, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Initial experiments on flutter of unswept cantilever wings at Mach number 1.3

Initial experiments on flutter of unswept cantilever wings at Mach number 1.3

Date: January 6, 1949
Creator: Tuovila, W J; Baker, John E & Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed wind-tunnel investigation of a sweptback wing with an added triangular area at the center

High-speed wind-tunnel investigation of a sweptback wing with an added triangular area at the center

Date: January 14, 1949
Creator: Henry, Beverly, Z , jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of 24-inch supersonic axial-flow compressor in air II : performance of compressor rotor at equivalent tip speeds from 800 to 1765 feet per second

Performance of 24-inch supersonic axial-flow compressor in air II : performance of compressor rotor at equivalent tip speeds from 800 to 1765 feet per second

Date: January 21, 1949
Creator: Johnsen, Irving A; Wright, Linwood C & Hartmann, Melvin J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Date: January 26, 1949
Creator: Madden, Robert T
Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation of a large-scale model at low speed

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation of a large-scale model at low speed

Date: January 21, 1949
Creator: Mccormack, Gerald M & Walling, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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