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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1931
 Collection: National Advisory Committee for Aeronautics Collection
Advantages of oxide films as bases for aluminum pigmented surface coatings for aluminum alloys

Advantages of oxide films as bases for aluminum pigmented surface coatings for aluminum alloys

Date: November 1, 1931
Creator: Buzzard, R W & Mutchler, W H
Description: Both laboratory and weather-exposure corrosion tests showed conclusively that the protection afforded by aluminum pigmented spar varnish coatings applied to previously anodized aluminum surfaces was greatly superior to that afforded by the same coatings applied to surfaces which had simply been cleaned free from grease and not anodized.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of six commonly used Airfoils over a large range of positive and negative angles of attack

The aerodynamic characteristics of six commonly used Airfoils over a large range of positive and negative angles of attack

Date: November 1, 1931
Creator: Anderson, Raymond F
Description: This paper presents the results of tests of six commonly used airfoils: the CYH, the N-22, the C-72, the Boeing 106, and the Gottingen 398. The lifts, drags, and pitching moments of the airfoils were measured through a large range of positive and negative angles of attack. The tests were made in the variable density wind tunnel of the National Advisory Committee for Aeronautics at a large Boeing 106, and the Gottingen 398 airfoils, the negative maximum lift coefficients were found to be approximately half the positive; but for the M-6 and the CYH, which have less effective values were, respectively, 0.8 and 0.6 of the positive values.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of three tapered airfoils tested in the variable density wind tunnel

The aerodynamic characteristics of three tapered airfoils tested in the variable density wind tunnel

Date: February 1, 1931
Creator: Anderson, Raymond F
Description: This report contains the lift, drag, and moment characteristics of tapered Clark Y, Gottingen 393, and USA 45 airfoils as obtained from tests made in the Variable Density Wind Tunnel of the NACA. The results are given at both low and high Reynolds Numbers to show scale effect and to provide data for use in airplane design.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic wind vane and the inherent stability of airplanes

The aerodynamic wind vane and the inherent stability of airplanes

Date: February 1, 1931
Creator: Lapresle, A
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical education and research at the Swiss Institute of Technology in Zurich

Aeronautical education and research at the Swiss Institute of Technology in Zurich

Date: April 1, 1931
Creator: Karner, L & Ackeret, J
Description: Progress in the scientific and practical fields of aviation has caused the Swiss Institute of Technology to organize lectures and practical training courses in all three branches of aeronautics and to found centers of scientific research, laboratories, etc., in order to supply the government and industries with scientifically and technically trained engineers.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft accidents : method of analysis

Aircraft accidents : method of analysis

Date: January 1, 1931
Creator: unknown
Description: The revised report includes the chart for the analysis of aircraft accidents, combining consideration of the immediate causes, underlying causes, and results of accidents, as prepared by the special committee, with a number of the definitions clarified. A brief statement of the organization and work of the special committee and of the Committee on Aircraft Accidents; and statistical tables giving a comparison of the types of accidents and causes of accidents in the military services on the one hand and in civil aviation on the other, together with explanations of some of the important differences noted in these tables.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft woods: their properties, selection, and characteristics

Aircraft woods: their properties, selection, and characteristics

Date: January 1, 1931
Creator: Markwardt, L J
Description: Strength values of various woods for aircraft design for a 15 per cent moisture condition of material and a 3-second duration of stress are presented, and also a discussion of the various factors affecting the values. The toughness-test method of selecting wood is discussed, and a table of acceptance values for several species is given.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil pressure distribution investigation in the variable density wind tunnel

Airfoil pressure distribution investigation in the variable density wind tunnel

Date: January 1, 1931
Creator: Jacobs, Eastman N; Stack, John & Pinkerton, Robert M
Description: Report presents the results of wind tunnel tests of pressure distribution measurements over one section each of six airfoils. Pressure distribution diagrams, as well as the integrated characteristics of the airfoils, are given for both a high and a low dynamic scale or, Reynolds number VL/V, for comparison with flight and other wind-tunnel tests, respectively. It is concluded that the scale effect is very important only at angles of attack near the burble. The distribution of pressure over an airfoil having a Joukowski section is compared with the theoretically derived distribution. A further study of the distribution of pressure over all of the airfoils resulted in the development of an approximate method of predicting the pressure distribution along the chord of any normal airfoil for all attitudes within the working range if the distribution at one attitude is known.
Contributing Partner: UNT Libraries Government Documents Department
Airplane landing gear

Airplane landing gear

Date: July 1, 1931
Creator: Maiorca, Salvatore
Description: This report presents an investigation of the design and construction of various types of landing gears. Some of the items discussed include: chassises, wheels, shock absorbers (rubber disk and rubber cord), as well as oleopneumatic shock absorbers. Various types of landing gears are also discussed such as the Messier, Bendix, Vickers, and Bleriot.
Contributing Partner: UNT Libraries Government Documents Department
The Amiot 140 M military airplane (French) : an all-metal multiplace high-wing monoplane

The Amiot 140 M military airplane (French) : an all-metal multiplace high-wing monoplane

Date: February 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (16th).administrative report including Technical Reports nos. 337 to 364

Annual report of the National Advisory Committee for Aeronautics (16th).administrative report including Technical Reports nos. 337 to 364

Date: January 1, 1931
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Contributing Partner: UNT Libraries Government Documents Department
The Avro 627 "Mailplane" (English): A Single-Seat Biplane

The Avro 627 "Mailplane" (English): A Single-Seat Biplane

Date: August 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Basic requirements of fuel-injection nozzles for quiescent combustion chambers

Basic requirements of fuel-injection nozzles for quiescent combustion chambers

Date: June 1, 1931
Creator: Spanogle, J A & Foster, H H
Description: This report presents test results obtained during an investigation of the performance of a single-cylinder, high-speed, compression-ignition test engine when using multiple-orifice fuel-injection valve nozzles in which the number and the direction of the orifices were varied independently.
Contributing Partner: UNT Libraries Government Documents Department
The behavior of conventional airplanes in situations thought to lead to most crashes

The behavior of conventional airplanes in situations thought to lead to most crashes

Date: February 1, 1931
Creator: Weick, Fred E
Description: Simple flight tests were made on ten conventional airplanes for the purpose of determining their action in the following two situations, which are generally thought to precede and lead to a large proportion of airplane crashes.
Contributing Partner: UNT Libraries Government Documents Department
The Bernard 80 G.R. long-distance airplane (French) : a two-place cantilever monoplane

The Bernard 80 G.R. long-distance airplane (French) : a two-place cantilever monoplane

Date: July 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Bernard 120 seaplane (French) : a 1400 hp single-seat monoplane racer

The Bernard 120 seaplane (French) : a 1400 hp single-seat monoplane racer

Date: March 1, 1931
Creator: Leglise, Pierre
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Bleriot 110 airplane (French) : a long-distance high-wing monoplane

The Bleriot 110 airplane (French) : a long-distance high-wing monoplane

Date: March 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Breguet 390 T commercial airplane (French) : a ten-seat all-steel sesquiplane

Breguet 390 T commercial airplane (French) : a ten-seat all-steel sesquiplane

Date: August 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Breguet military airplane, type 33 : a two-place long-distance sesquiplane for observation and bombing

Breguet military airplane, type 33 : a two-place long-distance sesquiplane for observation and bombing

Date: September 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The C.A.M.S. 60 seaplane (French) : a twin-engine bombing and torpedo monoplane

The C.A.M.S. 60 seaplane (French) : a twin-engine bombing and torpedo monoplane

Date: April 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Clerget 100 hp heavy-oil engine

Clerget 100 hp heavy-oil engine

Date: January 1, 1931
Creator: Leglise, Pierre
Description: A complete technical description of the Clerget heavy-oil engine is presented along with the general characteristics. The general characteristics are: 9 cylinders, bore 120 mm, stroke 130 mm, four-stroke cycle engine, rated power limited to 100 hp at 1800 rpm; weight 228 kg; propeller with direct drive and air cooling. Moving parts, engine block, and lubrication are all presented.
Contributing Partner: UNT Libraries Government Documents Department
Combined pitching and yawing motion of airplanes

Combined pitching and yawing motion of airplanes

Date: May 1, 1931
Creator: Hopf, L & Baranoff, A V
Description: This report treats the following problems: The beginning of the investigated motions is always a setting of the lateral controls, i.e., the rudder or the ailerons. Now, the first interesting question is how the motion would proceed if these settings were kept unchanged for some time; and particularly, what upward motion would set in, how soon, and for how long, since therein lie the dangers of yawing. Two different motions ensue with a high rate of turn and a steep down slope of flight path in both but a marked difference in angle of attack and consequently different character in the resultant aerodynamic forces: one, the "corkscrew" dive at normal angle, and the other, the "spin" at high angle.
Contributing Partner: UNT Libraries Government Documents Department
Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger

Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger

Date: January 1, 1931
Creator: Schey, Oscar W & Young, Alfred W
Description: This report presents the comparative flight results of a roots supercharger and a turbocentrifugal supercharger. The tests were conducted using a modified DH-4M2 airplane. The rate of climb and the high speed in level flight of the airplane were obtained for each supercharger from sea level to the ceiling. The unsupercharged performance with each supercharger mounted in place was also determined. The results of these tests show that the ceiling and rate of climb obtained were nearly the same for each supercharger, but that the high speed obtained with the turbocentrifugal was better than that obtained with the roots. The high-speed performance at 21,000 feet was 122 and 142 miles per hour for the roots and turbocentrifugal, respectively.
Contributing Partner: UNT Libraries Government Documents Department
A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel

A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel

Date: August 1, 1931
Creator: Defoe, George L
Description: An investigation was made of the aerodynamic effects of reflexing the trailing edge of three commonly used airfoils. Six airfoils were used in the investigation: three having the normal profiles of the Navy 60, the Boeing 106, and the Gottingen 398, and three having these profiles modified to obtain a reflexed trailing edge with the mean camber line changed to give Cmc/4=0. The tests were conducted at a value of the Reynolds Number of approximately 3,100,000 in the variable density wind tunnel of the National Advisory Committee for Aeronautics. Measurements of lift, drag, and pitching moment were made on each of the six airfoils. The expected reduction of the center of pressure travel was obtained. The maximum lift was reduced approximately 12 per cent and the minimum profile drag approximately 4 per cent.
Contributing Partner: UNT Libraries Government Documents Department
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