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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
 Collection: Technical Report Archive and Image Library
Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane

Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane

Date: March 1, 1929
Creator: unknown
Description: Equipped with a 40 HP Salmson engine, it is a single seat parasol type construction.
Contributing Partner: UNT Libraries Government Documents Department
Nieuport-Delage 640 (French) : commercial high-wing monoplane

Nieuport-Delage 640 (French) : commercial high-wing monoplane

Date: March 1, 1929
Creator: unknown
Description: The Nieuport Delage 640 is a single engine commercial high-wing monoplane of all wood construction, including the fuselage and tail. It's landing gear is hinged in two parts.
Contributing Partner: UNT Libraries Government Documents Department
Liore-Olivier airplane : type 12 night-bomber or type 20 commercial

Liore-Olivier airplane : type 12 night-bomber or type 20 commercial

Date: March 1, 1926
Creator: Serryer, J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Francois Villiers marine pursuit airplane

The Francois Villiers marine pursuit airplane

Date: April 1, 1927
Creator: Serryer, J
Description: A traditional biplane design allows this craft to function with the speed and maneuverability necessary to perform as a pursuit aircraft while also being able to land on water. It featured retractable landing gear for water landings. It was powered with a 450 HP. Lorraine-Dietrich engine.
Contributing Partner: UNT Libraries Government Documents Department
The Westland IV commercial monoplane (British)three "Cirrus III" engine

The Westland IV commercial monoplane (British)three "Cirrus III" engine

Date: April 1, 1929
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Short "Calcutta" : first British all-metal commercial seaplane

The Short "Calcutta" : first British all-metal commercial seaplane

Date: March 1, 1928
Creator: unknown
Description: The Calcutta is a large seaplane, with seating for 16 and a payload of 3,400 pounds.
Contributing Partner: UNT Libraries Government Documents Department
Bleriot-Spad 91 Airplane (French) : pursuit single-seater, type "Jockey"

Bleriot-Spad 91 Airplane (French) : pursuit single-seater, type "Jockey"

Date: May 1, 1928
Creator: SOCIETE BLERIOT-AERONAUTIQUE
Description: This aircraft has announced a speed of 270 km per hour at 4000 m. It is of all metal construction.
Contributing Partner: UNT Libraries Government Documents Department
Two 'Gloster' Airplanes : the 'Grouse II,' - Two-Seat Training Airplane. The 'Grebe II,' Single-Seat Fighter

Two 'Gloster' Airplanes : the 'Grouse II,' - Two-Seat Training Airplane. The 'Grebe II,' Single-Seat Fighter

Date: June 1, 1926
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the experimental aerodynamic loading on a model helicopter rotor blade

An investigation of the experimental aerodynamic loading on a model helicopter rotor blade

Date: May 1, 1953
Creator: Meyer, John R , Jr; Falabella, Gaetano, Jr & NACA
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lockheed "Vega" airplane : a commercial cabin monoplane

Lockheed "Vega" airplane : a commercial cabin monoplane

Date: November 1, 1927
Creator: unknown
Description: The Vega is a high wing monoplane suitable for commercial purposes. It can seat 6 passengers or 100 cubic feet of cargo.
Contributing Partner: UNT Libraries Government Documents Department
The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

Date: August 1, 1927
Creator: unknown
Description: The Widgeon III is a parasol type monoplane. One of it's strongest features was the high degree of visibility available to the pilot.
Contributing Partner: UNT Libraries Government Documents Department
The Mureaux "Brunet 3C2" pursuit airplane

The Mureaux "Brunet 3C2" pursuit airplane

Date: May 1, 1927
Creator: Serryer, J
Description: Designed by Engineer Brunet, the 3C2 is an all metal monoplane with two engines and provision for six machine guns and 12 10 Kg. bombs.
Contributing Partner: UNT Libraries Government Documents Department
The Armstrong Whitworth "Starling" (British) : (single seat fighter)

The Armstrong Whitworth "Starling" (British) : (single seat fighter)

Date: September 1, 1928
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Date: March 15, 1954
Creator: Von Glahn, Uwe H & Gray, Vernon H
Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the stagnation region caused a negligible change in drag compared with a completely unheated airfoil. Cyclic de-icing when properly applied caused the drag to decrease almost to the bare-airfoil drag value.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Date: July 22, 1952
Creator: Stewart, Warner L; Schum, Harold J & Wong, Robert Y
Description: The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking.
Contributing Partner: UNT Libraries Government Documents Department
The physical effects of detonation in a closed cylindrical chamber

The physical effects of detonation in a closed cylindrical chamber

Date: January 1, 1935
Creator: Draper, C S
Description: Detonation in the internal-combustion engine is studied as a physical process. It is shown that detonation is accompanied by pressure waves within the cylinder charge. Sound theory is applied to the calculation of resonant pressure-wave frequencies. Apparatus is described for direct measurement of pressure-wave frequencies. Frequencies determined from two engines of different cylinder sizes are shown to agree with the values calculated from sound theory. An outline of the theoretically possible modes of vibration in a right circular cylinder with flat ends is included. An appendix by John P. Elting gives a method of calculating pressure in the sound wave following detonation.
Contributing Partner: UNT Libraries Government Documents Department
General airplane performance

General airplane performance

Date: January 1, 1939
Creator: Rockfeller, W C
Description: Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations will for the most part apply to any type of engine-propeller combination and system of control, the only additional material required consisting of the actual engine and propeller curves for propulsion unit. Finally, a more exact method for the calculation of the climb characteristics for the constant-speed controllable propeller is presented in the appendix.
Contributing Partner: UNT Libraries Government Documents Department
Elastic instability of members having sections common in aircraft construction

Elastic instability of members having sections common in aircraft construction

Date: January 1, 1932
Creator: Trayer, George W & March, H W
Description: Two fundamental problems of elastic stability are discussed in this report. In part one formulas are given for calculating the critical stress at which a thin, outstanding flange of a compression member will either wrinkle into several waves or form into a single half wave and twist the member about its longitudinal axis. A mathematical study of the problem, which together with experimental work has led to these formulas, is given in an appendix. Results of test substantiating the recommended formulas are also presented. In part two the lateral buckling of beams is discussed. The results of a number of mathematical studies of this phenomenon have been published prior to this writing, but very little experimentally determined information relating to the problem has been available heretofore. Experimental verification of the mathematical deductions is supplied.
Contributing Partner: UNT Libraries Government Documents Department
Air propellers in yaw

Air propellers in yaw

Date: January 1, 1937
Creator: Lesley, E P; Worley, George F & Moy, Stanley
Description: Report presents the results of tests conducted at Stanford University of a 3-foot model propeller at four pitch settings and at 0 degree, 10 degrees, 20 degrees, and 30 degrees yaw. In addition to the usual propeller coefficients, cross-wind and vertical forces and yawing, pitching, and rolling moments were determined about axes having their origin at the intersection of the blade axis and the axis of rotation. The tests showed that the maximum efficiency was reduced only slightly for angles of yaw up to 10 degrees but that at 30 degrees yaw the loss in efficiency was about 10 percent. In all cases the cross-wind force was found to be greater than the cross-wind component of the axial thrust. With a yawed propeller an appreciable thrust was found for v/nd for zero thrust at zero yaw. Yawing a propeller was found to induce a pitching moment that increased in magnitude with yaw.
Contributing Partner: UNT Libraries Government Documents Department
Application of practical hydrodynamics to airship design

Application of practical hydrodynamics to airship design

Date: January 1, 1933
Creator: Upson, Ralph H & Klikoff, W A
Description: The purpose of the first two parts of this report is to present in concise format all the formulas required for computation of the hydrodynamic forces, so that they can be easily computed for either straight or curvilinear flight. Improved approximations are also introduced having a high degree of accuracy throughout the entire range of practical proportions. The remaining two parts of the report are devoted respectively to stability and skin friction, as functions of the same hydrodynamic forces.
Contributing Partner: UNT Libraries Government Documents Department
A proof of the theorem regarding the distribution of lift over the span for minimum induced drag

A proof of the theorem regarding the distribution of lift over the span for minimum induced drag

Date: January 1, 1931
Creator: Durand, W F
Description: The proof of the theorem that the elliptical distribution of lift over the span is that which will give rise to the minimum induced drag has been given in a variety of ways, generally speaking too difficult to be readily followed by the graduate of the average good technical school of the present day. In the form of proof this report makes an effort to bring the matter more readily within the grasp of this class of readers.
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
A method of calculating the ultimate strength of continuous beams

A method of calculating the ultimate strength of continuous beams

Date: January 1, 1931
Creator: Newlin, J A & Trayer, George W
Description: The purpose of this study was to investigate the strength of continuous beams after the elastic limit has been passed. As a result, a method of calculation, which is applicable to maximum load conditions, has been developed. The method is simpler than the methods now in use and it applies properly to conditions where the present methods fail to apply.
Contributing Partner: UNT Libraries Government Documents Department
Stability of thin-walled tubes under torsion

Stability of thin-walled tubes under torsion

Date: January 1, 1935
Creator: Donnell, L H
Description: In this report a theoretical solution is developed for the torsion on a round thin-walled tube for which the walls become unstable. The results of this theory are given by a few simple formulas and curves which cover all cases. The differential equations of equilibrium are derived in a simpler form than previously found, it being shown that many items can be neglected.
Contributing Partner: UNT Libraries Government Documents Department
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