Serial/Series Title
NACA Research Memorandums
412
NACA Technical Notes
327
NACA Technical Memorandums
105
NACA Wartime Reports
104
NACA Technical Reports
62
NACA Advanced Restricted Reports
46
NACA Advanced Confidential Reports
29
NACA Restricted Bulletins
17
NACA Aircraft Circulars
16
NACA Memorandum Reports
16
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1,040 Matching Results
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Foaming Volume and Foam Stability
"A method of measuring foaming volume is described and investigated to establish the critical factors in its operation. Data on foaming volumes and foam stabilities are given for a series of hydrocarbons and for a range of concentrations of aqueous ethylene-glycol solutions. It is shown that the amount of foam formed depends on the machinery of its production as well as on properties of the liquid, whereas the stability of the foam produced, within specified mechanical limitations, is primarily a function of the liquid" (p. 1).
Date:
February 1947
Creator:
Ross, Sydney
System:
The UNT Digital Library
Flight Measurements of the Lateral Control Characteristics of Narrow-Chord Ailerons on the Trailing Edge of a Full-Span Slotted Flap
Note presenting results of flight tests made to determine the effect of flap deflection on the lateral control characteristics of a modified Brewster F2A-2 airplane equipped with partial-span narrow-chord ailerons on the trailing edge of a full-span NACA slotted flap. The results indicated that the effectiveness of the ailerons was greatly reduced at flap deflections greater than about 20 degrees.
Date:
February 1947
Creator:
Sawyer, Richard H.
System:
The UNT Digital Library
A Comparison of the Lateral Motion Calculated for Tailless and Conventional Airplanes
Theoretical analysts of lateral dynamic motion of tailless and conventional airplanes was made for fighter and heavy transport. Their reactions to a lateral gust and control power required by each for simple maneuvers were determined and compared. Both types of airplanes require almost identical aileron control power to perform a given maneuver; tailless airplane requires about 1-2 to 1-3 directional control power of conventional airplane. Tailless airplane also shows greatest displacement for a given disturbance and has least damping in oscillatory mode.
Date:
February 1947
Creator:
Harper, Charles W. & Jones, Arthur L.
System:
The UNT Digital Library
Effects of Partial Admission on Performance of a Gas Turbine
Report presenting an investigation of the effect of partial admission of the driving fluid on the performance of a representative full-admission, production-type gas turbine. Results regarding losses, full-admission performance, partial-admission performance, partial admission as a means of power control, and a comparison of partial admission with other methods of power control are provided.
Date:
February 1949
Creator:
Kohl, Robert C.; Herzig, Howard Z. & Whitney, Warren J.
System:
The UNT Digital Library
Method for Evaluating From Shadow or Schlieren Photographs the Pressure Drag in Two-Dimensional or Axially Symmetrical Flow Phenomena With Detached Shock
"A method has been developed for evaluating from shadow or schileren photographs the pressure drag of axially symmetrical bodies at zero angle of attack or of two-dimensional bodies producing detached shock. The method consists in the determination of the flow properties along a characteristic line and the application of the momentum theorem to a stream tube around the body. The method can be applied to the determination of external drag of supersonic inlets with subsonic flow at the entrance of the inlet" (p. 1).
Date:
February 1949
Creator:
Ferri, Antonio
System:
The UNT Digital Library
The application of airfoil studies to helicopter rotor design
From Summary: "In order to facilitate the application of miscellaneous airfoil data to the problems of the helicopter designer, a discussion of a number of the problems most frequently arising is presented. A reference list of published papers on airfoil section characteristics (or their application) which experience has shown to be useful in connection with these helicopter problems is included."
Date:
February 1949
Creator:
Gustafson, F. B.
System:
The UNT Digital Library
A study of flow changes associated with airfoil section drag rise at supercritical speeds
Report presenting a study of experimental pressure distributions and section characteristics for several moderately thick airfoil sections were made. The pressure distributions and section force characteristics of several moderately thick airfoil sections at Mach numbers above the drag-divergence Mach numbers were analyzed.
Date:
February 1949
Creator:
Nitzberg, Gerald E. & Crandall, Stewart
System:
The UNT Digital Library
Effects of Several Design Variables on Turbine-Wheel Weight
Report presenting an analysis showing the effect of several design variables on turbine-wheel flight. Equations are developed for the calculations of weights of the disk, the rim, and the blades, and use the following variables: the blading aspect ratio and solidity, the ratio of the centrifugal stress at the blade roots to that in the disk, and the ratio of wheel diameter at the blade root to wheel diameter at the blade tip.
Date:
February 1949
Creator:
LaValle, Vincent L. & Huppert, Merle C.
System:
The UNT Digital Library
Performance of axial-flow fan and compressor blades designed for high loadings
Report presenting an investigation to determine the effects of loading on the performance of axial-flow fan and compressor blades in a test blower. Results regarding verification of the two-dimensional design data and effects of blade roughness are provided.
Date:
February 1947
Creator:
Bogdonoff, Seymour M. & Herrig, L. Joseph
System:
The UNT Digital Library
On Compressibility Corrections for Subsonic Flow Over Bodies of Revolution
"A study of the subsonic flow past an infinitely long corrugated circular cylinder is presented to show the relation between two-dimensional and axisymmetrical flow. In fact, a solution is obtained which contains as limiting cases both the Prandtl-Glauert correction for two-dimensional flow and the Göthert correction for flow past slender bodies of revolution. Included in the paper are velocity-correction formulas for a cylinder with a single bump and for a corrugated cylinder in the presence of walls" (p. 1).
Date:
February 1949
Creator:
Reissner, Eric
System:
The UNT Digital Library
Triangular wings cambered and twisted to support specified distributions of lift at supersonic speeds
Report presenting an application of the linearized supersonic flow theory to the calculation of the camber and twist required for various lift distributions on a triangular wing with leading edges behind the Mach cone. Several specific examples are used and plots of the cambered surfaces, corresponding lift distributions, and values of the theoretical drag coefficients are presented.
Date:
February 1949
Creator:
Baldwin, Barrett S., Jr.
System:
The UNT Digital Library
In-line aircraft-engine bearing loads 3: main-bearing loads
Report presenting the application of dimensional analysis to the computation of the main bearing of a V-type in-line aircraft engine. Two crankshafts have been considered, one designed for higher operating speed than the other. Two types of engines are considered: one for regular V-type engines and one for production V-type engines.
Date:
February 1947
Creator:
Shaw, Milton C. & Macks, E. Fred
System:
The UNT Digital Library
The Response of Pressure Measuring Systems to Oscillating Pressures
Note presenting a method for calculating the response and lag in pressure measuring systems subjected to steady-state sinusoidally varying pressures. The pressure system is assumed to consist of an inlet restriction, tubing length, and connected instrument volume. Results of the phase-shift determination are provided.
Date:
February 1949
Creator:
Taback, Israel
System:
The UNT Digital Library
The synthesis of methylenecyclobutane, spiropentane, and 2-methyl-1-butene from pentaerythrityl tetrabromide
From Summary: "Reduction of pentaerythrityl tetrabromide in ethanol with zinc in the presence of sodium carbonate and sodium iodide was found to yield methylenecyclobutane, spiropentane, and 2-methyl-l-butene. Yields were 46 percent methylenecyclobutane, 21 percent spiropentane, and 12 percent 2-methyl-l-butene. The reduction procedure described offers a method of preparing both methylenecyclobutane and spiropentane from the same reaction in yields comparable with individual methods of synthesis previously reported."
Date:
February 1946
Creator:
Slabey, Vernon A.
System:
The UNT Digital Library
Aeronautic Instruments
"The development of aeronautic instruments. Vibrations, rapid changes of the conditions of flight and of atmospheric conditions, influence of the air stream all call for particular design and construction of the individual instruments. This is shown by certain examples of individual instruments and of various classes of instruments for measuring pressure, change of altitude, temperature, velocity, inclination and turning or combinations of these" (p. 1).
Date:
February 1924
Creator:
Everling, E. & Koppe, H.
System:
The UNT Digital Library
The laboratories of the Technical Section of Aeronautics (Service Technique de L'Aeronautique or S.T.Ae.)
An historical sketch of the laboratories of the Technical Section is provided. A breakdown of the different departments and their specialties is also listed.
Date:
February 1923
Creator:
Robert
System:
The UNT Digital Library
"AM" Flexible Metal Joint
A flexible metal joint used for connecting fuel lines is investigated and methods for assembly are included.
Date:
February 1923
Creator:
unknown
System:
The UNT Digital Library
Relation Between the Stability Characteristics and the Controllability of German Airplanes
This survey is intended to give a general approximate idea of the stability and controllability of German airplanes. Both flight characteristics, including the behavior of the airplane under the action of deflected controls and external disturbances, and flight performance, which refers to climbing, speed, take-off, and landing qualities.
Date:
February 1930
Creator:
Hübner, Walter
System:
The UNT Digital Library
Experimental Investigations Concerning the Limits of Detonation in Gaseous Mixtures: Part 1
Memorandum presenting an investigation to determine quantitatively the limits of detonation in gaseous mixtures for the conditions imposed and for a number of given gaseous explosive mixtures.
Date:
February 1930
Creator:
Wendlandt, Rudolf
System:
The UNT Digital Library
Fixed Air-Cooled Engines
"It is proposed to analyze the advantages and disadvantages of large fixed air-cooled radial engines and to explain how the problems have been solved by the Bristol Aeroplane Company" (p. 1).
Date:
February 1923
Creator:
Fedden, A. H.
System:
The UNT Digital Library
"Am" Gasoline Cock
The "AM" cock was designed specially for gasoline pipes on vehicles using internal combustion engines (airplanes, airships, automobiles, tractors, battle "tanks", boats, etc.). The report descirbes the functioning and construction of the device.
Date:
February 1923
Creator:
unknown
System:
The UNT Digital Library
Magnan Glider M-2
The construction of the Magnan glider, M-2, is presented which is designed to fly in so-called horizontal winds. Details of the wings, fuselage, tail surfaces, controls, landing gear, characteristics, operation, photographs, and drawings are provided.
Date:
February 1924
Creator:
Lesage, M. André
System:
The UNT Digital Library
The Use of Elektron Metal in Airplane Construction
Memorandum presenting an evaluation of elektron, which is the lightest of the light metals and is of particular interest for aircraft construction. Some of its chemical properties, particular alloys and wrought materials that can be made using elektron, and some of the potential ways in which the material might be used are provided.
Date:
February 1931
Creator:
de Ridder, E. I.
System:
The UNT Digital Library
The Aerodynamic Wind Vane and the Inherent Stability of Airplanes
Report discussing the design of the wind vane described rests on the following line of reasoning: An airplane, originally in equilibrium about its C.G. is assumed to be deflected from this position through an angle (delta)i, the variation (delta)i being so sudden that the path of the C.G. and the airplane speed do not change while it is taking place. The aerodynamic forces acting on the wings, tail surfaces, fuselage, etc., which, as a whole, exerted a zero moment (M(sub G) = 0) about the center of gravity at the instant of equilibrium, now exert a moment M(sub G) not equal to 0.
Date:
February 1931
Creator:
Lapresle, A.
System:
The UNT Digital Library