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 Collection: National Advisory Committee for Aeronautics Collection
The 300 H.P. Benz Aircraft Engine

The 300 H.P. Benz Aircraft Engine

Date: January 1921
Creator: Heller, A.
Description: This report provides a description of the Benz 300 H.P. aircraft engine containing 12 cylinders placed at a 60° angle. It includes a detailed description of the development of the constructional points, particularly the cylinders, pistons, and connecting rods, as well as the engine fitting, lubrication, oil pumps, bearings, oil tank, fuel pump, carburetors, and cooling system. There are seven pages of illustrative figures at the end of the report.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a 20-inch-diameter ram-jet engine investigated in a free-jet facility at Mach number 3.0

Altitude performance of a 20-inch-diameter ram-jet engine investigated in a free-jet facility at Mach number 3.0

Date: January 1, 1952
Creator: Smolak, G. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design of combustor for long-range ram-jet engine and performance of rectangular analog

Design of combustor for long-range ram-jet engine and performance of rectangular analog

Date: January 29, 1954
Creator: Koch, R. G.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary transient performance data on the fuel control of the XRJ47-W-5 ram-jet engine

Preliminary transient performance data on the fuel control of the XRJ47-W-5 ram-jet engine

Date: January 1, 1954
Creator: Smith, I. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser

Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser

Date: March 28, 1955
Creator: Farley, J. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine

Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine

Date: March 10, 1954
Creator: Meyer, C. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Propeller design I : practical application of the blade element theory

Propeller design I : practical application of the blade element theory

Date: May 1, 1926
Creator: Weick, Fred E
Description: This report is the first of a series of four on propeller design and contains a description of the blade elements or modified Drzewiecke theory as used in the Bureau of Aeronautics, U.S. Navy Department. Blade interference corrections are used which were taken from R.& M. NO. 639 of the British Advisory Committee for Aeronautics. The airfoil characteristics used were obtained from tests of model propellers, not from tests of model wings.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the characteristics of steel diaphragms for automatic fuel-injection valves

An investigation of the characteristics of steel diaphragms for automatic fuel-injection valves

Date: April 1, 1926
Creator: Joachim, W F
Description: This research on steel diaphragms was undertaken at the Langley Memorial Aeronautical Laboratory, as a part of a general investigation on fuel injection engines for aircraft. The work determined the load-deflection, load- deformation and hysteresis characteristics for single diaphragms having thicknesses from 0.00s inch to 0.012 inch, and for similar diaphragms tested in multiple having total thicknesses from 0.012 inch to 0.180 inch. The elastic limit loads and deflections, and rupture points of single diaphragms were also determined. Some work was done on diaphragms having central orifices in order to determine the effect of orifice diameter upon the load deflection characteristics.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of wing float displacement in single-float seaplanes

The calculation of wing float displacement in single-float seaplanes

Date: March 1, 1925
Creator: Warner, Edward P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A load factor formula

A load factor formula

Date: August 1, 1927
Creator: Miller, Roy G
Description: The ultimate test of a load factor formula is experience. The chief advantages of a semi rational formula over arbitrary factors are that it fairs in between points of experience and it differentiates according to variables within a type. Structural failure of an airplane apparently safe according to the formula would call for a specific change in the formula. The best class of airplanes with which to check a load factor formula seems to be those which have experienced structural failure. Table I comprises a list of the airplanes which have experienced failure in flight traceable to the wing structure. The load factor by formula is observed to be greater than the designed strength in each case, without a single exception. Table II comprises the load factor by formula with the designed strength of a number of well-known service types. The formula indicates that by far the majority of these have ample structural strength. One case considered here in deriving a suitable formula is that of a heavy load carrier of large size and practically no reserve power.
Contributing Partner: UNT Libraries Government Documents Department
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