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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

Date: November 1947
Creator: Reynolds, E E; Freeman, J W & White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Abstracts pertaining to seaplanes

Abstracts pertaining to seaplanes

Date: July 24, 1947
Creator: Bidwell, Jerold M & King, Douglas A
Description: About 400 references pertaining to the hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings.
Contributing Partner: UNT Libraries Government Documents Department
Acceleration Characteristics of R-3350 Engine Equipped with NACA Injection Impeller

Acceleration Characteristics of R-3350 Engine Equipped with NACA Injection Impeller

Date: January 8, 1947
Creator: Hickel, Robert O. & Snider, William E.
Description: Qualitative investigations have shown that use of the NACA injection impeller with the R-3350 engine increases the inertia of the fuel-injection system and, when the standard fuel-metering system is used, this increase in inertia results in poor engine acceleration characteristics. This investigation was therefore undertaken to determine whether satisfactory acceleration characteristics of the engine equipped with the injection impeller could be obtained by simple modifications to the fuel-monitoring system. The engine was operated with two types of carburetor; namely, a hydraulic-metering carburetor incorporating a vacuum-operated accelerating pump and a direct-metering carburetor having a throttle-actuated accelerating pump. The vacuum-operated accelerating pump of the hydraulic-metering carburetor was modified to produce satisfactory accelerations by supplementing the standard air chamber with an additional 75-cubic spring. The throttle-actuated accelerating pump of the direct-metering carburetor was modified to produce satisfactory accelerations by replacing the standard 0.028-inch-diameter bleed in the load-compensator balance line with a smaller bleed of 0.0225-inch diameter. The results of this investigation indicated that both carburetors can be easily modified to produce satisfactory acceleration characteristics of the engine and no definite choice between the types of carburetor and accelerating pump can be made. Use of the direct-metering carburetor, however, probably resulted in better fuel ...
Contributing Partner: UNT Libraries Government Documents Department
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. & Zeck, Howard
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
Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336

Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336

Date: September 25, 1947
Creator: Clement, Eugene P. & Havens, Robert F.
Description: A 1/5.5-size powered dynamic model of the Columbia XJL-1 amphibian was landed in Langley tank no. 1 in smooth water and in oncoming waves of heights from 2.1 feet to 6.4 feet (full-size) and lengths from 50 feet to 264 feet (full-size). The motions and the vertical accelerations of the model were continuously recorded. The greatest vertical acceleration measured during the smooth-water landings was 3.1g. During landings in rough water the greatest vertical acceleration measured was 15.4g, for a landing in 6.4-foot by 165-foot waves. The impact accelerations increased with increase in wave height and, in general, decreased with increase in wave length. During the landings in waves the model bounced into the air at stalled attitudes at speeds below flying speed. The model trimmed up to the mechanical trim stop (20 deg) during landings in waves of heights greater than 2.0 feet. Solid water came over the bow and damaged the propeller during one landing in 6.4-foot waves. The vertical acceleration coefficients at first impact from the tank tests of a 1/5.5-size model were in fair agreement with data obtained at the Langley impact basin during tests of a 1/2-size model of the hull.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations and bottom pressures measured on a B-24D airplane in a ditching test

Accelerations and bottom pressures measured on a B-24D airplane in a ditching test

Date: November 1944
Creator: Steiner, Margaret F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations measured at center of gravity and along span of the wing of a B-24D airplane in landing impacts

Accelerations measured at center of gravity and along span of the wing of a B-24D airplane in landing impacts

Date: August 1944
Creator: Westfall, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accuracy of airspeed measurements and flight calibration procedures

Accuracy of airspeed measurements and flight calibration procedures

Date: 1948
Creator: Huston, Wilber B
Description: The sources of error that may enter into the measurement of airspeed by pitot-static methods are reviewed in detail together with methods of flight calibration of airspeed installations. Special attention is given to the problem of accurate measurements of airspeed under conditions of high speed and maneuverability required of military airplanes. (author).
Contributing Partner: UNT Libraries Government Documents Department
Adaptor for measuring principal strains with Tuckerman strain gage

Adaptor for measuring principal strains with Tuckerman strain gage

Date: June 1943
Creator: Mcpherson, A E
Description: An adapter is described which uses three Tuckerman optical strain gages to measure the displacement of the three vortices of an equilateral triangle along lines 120 degrees apart. These displacements are substituted in well-known equations in order to compute the magnitude and direction of the principal strains. Tests of the adaptor indicate that principal strains over a gage length of 1.42 inch may be measured with a systematic error not exceeding 4 percent and a mean observational error of the order of + or minus 0.000006. The maximum observed error in strain was of the order of 0.00006. The directions of principal strains for unidirectional stress were measured with the adaptor with an average error of the order of 1 degree.
Contributing Partner: UNT Libraries Government Documents Department
Addition of heat to a compressible fluid in motion

Addition of heat to a compressible fluid in motion

Date: February 1945
Creator: Hicks, Bruce L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional abstracts pertaining to seaplanes

Additional abstracts pertaining to seaplanes

Date: March 9, 1948
Creator: Bidwell, J. M. & King, D. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional design charts relating to the stalling of tapered wings

Additional design charts relating to the stalling of tapered wings

Date: January 1943
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds

Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds

Date: November 24, 1948
Creator: Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An additional investigation of the high-speed lateral-control characteristics of spoilers

An additional investigation of the high-speed lateral-control characteristics of spoilers

Date: June 1945
Creator: Summers, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The additional-mass effect of plates as determined by experiments

The additional-mass effect of plates as determined by experiments

Date: 1941
Creator: Gracey, William
Description: The apparent increase in the inertia properties of a body moving in a fluid medium has been called the additional-mass effect. This report presents a resume of test procedures and results of experimental determinations of the additional-mass effect of flat plates. In addition to data obtained from various foreign sources and from a NACA investigation in 1933, the results of tests recently conducted by the National Advisory Committee for Aeronautics are included.
Contributing Partner: UNT Libraries Government Documents Department
Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps

Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps

Date: October 1941
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional results in a free-flight investigation of control effectiveness of full-span, 0.2-chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, aspect ratio, taper, and section thickne

Additional results in a free-flight investigation of control effectiveness of full-span, 0.2-chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, aspect ratio, taper, and section thickne

Date: April 23, 1948
Creator: Sandahl, Carl A & Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Adjustment of stick force by a nonlinear aileron-stick linkage

Adjustment of stick force by a nonlinear aileron-stick linkage

Date: November 1942
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy

The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy

Date: December 1943
Creator: Nielson, Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Date: September 1943
Creator: Luoma, Arvo A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body -- NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body -- NACA model 84 series

Date: 1943?
Creator: Parkinson, John B; Olson, Roland E; Draley, Eugene C & Luoma, Arvo A
Description: A series of related forms of flying-boat hulls representing various degrees of compromise between aerodynamic and hydrodynamic requirements was tested in Langley Tank No. 1 and in the Langley 8-foot high-speed tunnel. The purpose of the investigation was to provide information regarding the penalties in water performance resulting from further aerodynamic refinement and, as a corollary, to provide information regarding the penalties in range or payload resulting from the retention of certain desirable hydrodynamic characteristics. The information should form a basis for over-all improvements in hull form.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil

Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil

Date: January 1943
Creator: Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Date: October 1942
Creator: Liddell, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: October 1, 1948
Creator: Solomon, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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