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 Decade: 1940-1949
 Year: 1947
 Month: May
 Collection: National Advisory Committee for Aeronautics Collection
Acceleration Measurements During Landing in Rough Water of a 1/7-Scale Dynamic Model of Grumman XJR2F-1 Amphibian - Langley Tank Model 212, TED No. NACA 2378

Acceleration Measurements During Landing in Rough Water of a 1/7-Scale Dynamic Model of Grumman XJR2F-1 Amphibian - Langley Tank Model 212, TED No. NACA 2378

Date: May 6, 1947
Creator: Land, Norman S.
Description: Tests of a 1/7 size model of the Grumman XJR2F-1 amphibian were made in Langley tank no.1 to examine the landing behavior in rough water and to measure the normal and angular accelerations experienced by the model during these landings. All landings were made normal to the direction of wave advance, a condition assumed to produce the greatest accelerations. Wave heights of 4.4 and 8.0 inches (2.5 and 4.7 ft, full size) were used in the tests and the wave lengths were varied between 10 and 50 feet (70 and 350 ft, full size). Maximum normal accelerations of about 6.5g were obtained in 4.4 inch waves and 8.5g were obtained in 8.0 inch waves. A maximum angular acceleration corresponding to 16 radians per second per second, full size, was obtained in the higher waves. The data indicate that the airplane will experience its greatest accelerations when landing in waves of about 20 feet (140 ft, full size) in length.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Date: May 23, 1947
Creator: Neely, Robert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Date: May 6, 1947
Creator: Perone, Angelo
Description: A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in various conditions of surface deformation are presented in this report.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II : performance with water injection at compressor inlet

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II : performance with water injection at compressor inlet

Date: May 19, 1947
Creator: Dietz, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Appreciation and determination of the hydrodynamic qualities of seaplanes

Appreciation and determination of the hydrodynamic qualities of seaplanes

Date: May 1, 1947
Creator: Parkinson, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bending stresses due to torsion in a tapered box beam

Bending stresses due to torsion in a tapered box beam

Date: May 1, 1947
Creator: Kruszewski, Edwin T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-induced upwash for yawed and swept-back wings in closed circular wind tunnels

Boundary-induced upwash for yawed and swept-back wings in closed circular wind tunnels

Date: May 1, 1947
Creator: Eisenstadt, Bertram J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculations of the supersonic wave drag of nonlifting wings with arbitrary sweepback and aspect ratio : wings swept behind the Mach lines

Calculations of the supersonic wave drag of nonlifting wings with arbitrary sweepback and aspect ratio : wings swept behind the Mach lines

Date: May 1, 1947
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for stress analysis of reinforced circular cylinders under lateral loads

Charts for stress analysis of reinforced circular cylinders under lateral loads

Date: May 1, 1947
Creator: Kempner, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Collection and analysis of wind-tunnel data on the characteristics of isolated tail surfaces with and without end plates

Collection and analysis of wind-tunnel data on the characteristics of isolated tail surfaces with and without end plates

Date: May 1, 1947
Creator: Bates, William R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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