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 Decade: 1940-1949
 Year: 1948
 Collection: National Advisory Committee for Aeronautics Collection
Tables and Charts of Flow Parameters Across Oblique Shocks

Tables and Charts of Flow Parameters Across Oblique Shocks

Date: August 1948
Creator: Neice, Mary M.
Description: Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy.
Contributing Partner: UNT Libraries Government Documents Department
Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Date: June 1948
Creator: Kuo, Yung-Huai
Description: The methods of NACA TN No. 995 have been slightly modified and extended in include flows with circulation by considering the alteration of the singularities of the incompressible solution due to the presence of the hypergeometric functions in the analytic continuation of the solution. It was found that for finite Mach numbers the only case in which the nature of the singularity can remain unchanged is for a ratio of specific heats equal to -1. From a study of two particular flows it seems that the effect of geometry cannot be neglected, and the conventional "pressure-correction" formulas are not valid, even in the subsonic region if the body is thick, especially if there is a supersonic region in the flow.
Contributing Partner: UNT Libraries Government Documents Department
Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

Date: July 1948
Creator: Huff, Vearl N. & Calvert, Clyde S.
Description: Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.
Contributing Partner: UNT Libraries Government Documents Department
Lifting-surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces

Lifting-surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces

Date: January 1, 1948
Creator: Crandall, Stewart M & Swanson, Robert S
Description: A limited number of lifting-surface-theory solutions for wings with chordwise loadings resulting from angle of attack, parabolic-ac camber, and flap deflection are now available. These solutions were studied with the purpose of determining methods of extrapolating the results in such a way that they could be used to determine lifting-surface-theory values of the aspect-ratio corrections to the lift and hinge-moment parameters for both angle-of-attack and flap-deflection-type loading that could be used to predict the characteristics of horizontal tail surfaces from section data with sufficient accuracy for engineering purposes. Such a method was devised for horizontal tail surfaces with full-span elevators. In spite of the fact that the theory involved is rather complex, the method is simple to apply and may be applied without any knowledge of lifting-surface theory. A comparison of experimental finite-span and section value and of the estimated values of the lift and hinge-moment parameters for three horizontal tail surfaces was made to provide an experimental verification of the method suggested. (author).
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-air parameters on combustion limit and flame length in 8-inch-diameter ram-jet combustion chamber

Effect of inlet-air parameters on combustion limit and flame length in 8-inch-diameter ram-jet combustion chamber

Date: July 22, 1948
Creator: Miller, R C & Cervenka, A J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Mach number on performance of an axial-flow compressor rotor-blade row

Effect of Mach number on performance of an axial-flow compressor rotor-blade row

Date: September 28, 1948
Creator: Dugan, Paul D; Mahoney, John J & Benser, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Date: November 17, 1948
Creator: Boksenbom, Aaron S & Novik, David
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and performance of experimental axial-discharge mixed-flow compressor II : performance of impeller

Design and performance of experimental axial-discharge mixed-flow compressor II : performance of impeller

Date: August 12, 1948
Creator: Wilcox, Ward W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and performance of experimental axial-discharge mixed-flow compressor I : impeller design theory

Design and performance of experimental axial-discharge mixed-flow compressor I : impeller design theory

Date: August 12, 1948
Creator: Goldstein, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades I : heat transfer from blades to cold air

Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades I : heat transfer from blades to cold air

Date: November 10, 1948
Creator: Meyer, Gene L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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