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Decade:
1940-1949
Collection:
National Advisory Committee for Aeronautics Collection
Effect of propeller-axis angle of attack on thrust distribution over the propeller disk in relation to wake-survey measurement of thrust
Date: December 1, 1945
Creator: Pendley, Robert E
Description: Tests were made to investigate the variation of thrust distribution over the propeller disk with angle of pitch of the propeller thrust axis and to determine the disposition and the minimum number of rakes necessary to measure the propeller thrust. The tests were made at a low Mach number for a low and a high blade angle with the propeller operating at three small angles of pitch, and some of the tests were repeated at a higher Mach number. The data obtained show that, for small angles of pitch, large changes occur in the energy distribution in the wake which prohibit the use of a single survey rake for thrust measurement in flight tests and limit the use of a single rake in wind-tunnel tests. Under certain conditions, the energy distribution in the wake took on a symmetrical form and two diametrically opposed survey rakes were shown to be satisfactory for obtaining propeller thrust. (author).
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65446/
Two dimensional wind-tunnel investigation of low drag vertical-tail,horizontal-tail, and wing sections equipped with sealed internally balanced control surfaces
Date: April 1, 1946
Creator: Braslow, Albert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65015/
Investigation of a variable Mach number supersonic tunnel with nonintersecting characteristics
Date: November 15, 1948
Creator: Evvard, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64572/
Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers III : normal-shock diffuser
Date: December 22, 1948
Creator: Schroeder, Albert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64571/
Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9
Date: October 28, 1948
Creator: Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64577/
Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades I : heat transfer from blades to cold air
Date: November 10, 1948
Creator: Meyer, Gene L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64576/
Investigation of effects of movable exhaust-nozzle plug on operational performance of 20-inch ram jet
Date: July 27, 1948
Creator: Sterbentz, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64606/
Wind-tunnel investigation of horizontal tails II : unswept and 35 degree swept-back plan forms of aspect ratio 4.5
Date: June 3, 1948
Creator: Dods, Jules B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64603/
A high-speed motion-picture study of normal combustion, knock and preignition in a spark-ignition engines
Date: January 1, 1941
Creator: Rothrock, A M
Description: Combustion in a spark-ignition engine was investigated by means of the NACA high-speed motion-picture cameras. This camera is operated at a speed of 40,000 photographs a second and therefore makes possible the study of changes that take place in the intervals as short as 0.000025 second. When the motion pictures are projected at the normal speed of 16 frames a second, any rate of movement shown is slowed down 2500 times. Photographs are presented of normal combustion, of combustion from preignitions, and of knock both with and without preignition. The photographs of combustion show that knock may be preceded by a period of exothermic reaction in the end zone that persists for a time interval of as much as 0.0006 second. The knock takes place in 0.00005 second or less.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc66365/
The calculated effect of various hydrodynamic and aerodynamic factors on the take-off of a large flying boat
Date: January 1, 1940
Creator: Olson, R E
Description: Report presents the results of an investigation made to determine the influence of various factors on the take-off performance of a hypothetical large flying boat by means of take-off calculations. The factors varied in the calculations were size of hull (load coefficient), wing setting, trim, deflection of flap, wing loading, aspect ratio, and parasite drag. The take-off times and distances were calculated to the stalling speeds and the performance above these speeds was separately studied to determine piloting technique for optimum take-off.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc66362/