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 Collection: National Advisory Committee for Aeronautics Collection
The problem of the turbo-compressor

The problem of the turbo-compressor

Date: August 1, 1920
Creator: Devillers, Rene
Description: In terminating the study of the adaptation of the engine to the airplane, we will examine the problem of the turbo-compressor,the first realization of which dates from the war; this will form an addition to the indications already given on supercharging at various altitudes. This subject is of great importance for the application of the turbo-compressor worked by the exhaust gases. As a matter of fact, a compressor increasing the pressure in the admission manifold may be controlled by the engine shaft by means of multiplication gear or by a turbine operated by the exhaust gas. Assuming that the increase of pressure in the admission manifold is the same in both cases, the pressure in the exhaust manifold would be greater in the case in which the compressor is worked by the exhaust gas and there would result a certain reduction of engine power which we must be able to calculate. On the other hand , if the compressor is controlled by the engine shaft, a certain fraction of the excess power supplied is utilized for the rotation of the compressor. In order to compare the two systems, it is there-fore necessary to determine the value of the reduction of ...
Contributing Partner: UNT Libraries Government Documents Department
Comparison and evaluation of two model techniques used in predicting bomb-release motions

Comparison and evaluation of two model techniques used in predicting bomb-release motions

Date: December 27, 1957
Creator: Carlson, H. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Date: November 1, 1951
Creator: Adams, Mac C.
Description: By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points. According to linearized theory, the optimum profiles are found to have infinite slope at the nose but zero radius of curvature so that the bodies appear to have pointed noses, a zero slope at the body base, and no variation of wave drag with Mach number. For those bodies having a specified intermediate.diameter (that is, location and magnitude given), the maximum body diameter is shown to be larger, in general, than the specified diameter. It is also shown that, for bodies having a specified maximum diameter, ...
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A

Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A

Date: September 27, 1957
Creator: Levey, G. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of ejection releases of submerged and semisubmerged dynamically scaled stores from a simulated bomb bay of a fighter- bomber airplane at supersonic speeds

An investigation of ejection releases of submerged and semisubmerged dynamically scaled stores from a simulated bomb bay of a fighter- bomber airplane at supersonic speeds

Date: December 26, 1956
Creator: Carter, H. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Longitudinal aerodynamic characteristics of various configurations of a revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01

Longitudinal aerodynamic characteristics of various configurations of a revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01

Date: May 4, 1956
Creator: Foster, G. V.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics

Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics

Date: November 27, 1956
Creator: Cesaro, R. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for calculating the lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds

A method for calculating the lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds

Date: November 12, 1953
Creator: Nielsen, Jack Norman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of circular shell-supported frames

Analysis of circular shell-supported frames

Date: May 1, 1944
Creator: Wignot, J. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Quasi-cylindrical theory of wing-body interfernece at supersonic speeds and comparison with experiment

Quasi-cylindrical theory of wing-body interfernece at supersonic speeds and comparison with experiment

Date: January 1, 1955
Creator: Nielsen, Jack Norman
Description: None
Contributing Partner: UNT Libraries Government Documents Department