UNT Libraries Government Documents Department - 236 Matching Results

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An analysis of flow in rotating passage of large radial-inlet centrifugal compressor at tip speed of 700 feet per second

Description: Report presenting an analysis of the flow in the rotating passages of a 48-inch diameter radial-inlet centrifugal impeller at a tip speed of 700 feet per second in order to provide more information on the flow conditions within the impeller. Results regarding the impeller and diffuser performance, design flow characteristics, and off-design flow characteristics are provided.
Date: December 1951
Creator: Prian, Vasily D. & Michel, Donald J.
Item Type: Refine your search to only Report
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Analysis of Pure-Bending Flutter of a Cantilever Swept Wing and Its Relation to Bending-Torsion Flutter

Description: From Introduction: "The present paper is intended to give some features of flutter in bending alone and contains results of analyses made to determine some effects of wing mass-density ratio, angle of sweepback, length-semichord ratio, and Mach number. Some relations of pure-blending flutter to the conventional bending-torsion flutter are also given."
Date: September 1951
Creator: Cunningham, H. J.
Item Type: Refine your search to only Report
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An Analytic Determination of the Flow Behind a Symmetrical Curved Shock in a Uniform Stream

Description: From Introduction: "The present report is concerned with a closer investigation of the validity of this method and includes a more complete formulation, as well as the computation procedure, of the series expansion. As stated in reference 1, the flow thus determined depends only on the Mach number when the detached distance is adopted as the length scale. General formulas and the procedure of calculation are given in this report for such purposes."
Date: October 1951
Creator: Lin, C. C. & Shen, S. F.
Item Type: Refine your search to only Report
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An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on a Flat Plate at Supersonic Speeds

Description: Report presenting a review of turbulent-boundary-layer analyses and experimental data for average skin-friction coefficients on a flat plate in high-speed flow. New solutions are presented which show the effect of using a continuous velocity gradient and the effect of the extent of the laminar sublayer on the average skin-friction coefficient.
Date: February 1951
Creator: Rubesin, Morris W.; Maydew, Randall C. & Varga, Steven A.
Item Type: Refine your search to only Report
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Analytical Investigation of Fully Developed Laminar Flow in Tubes With Heat Transfer With Fluid Properties Variable Along the Radius

Description: "In the analytical investigation reported herein, which was conducted in the NACA Lewis laboratory, both velocity and temperature distribution are obtained for fully developed laminar flow in tubes of gases and of liquid metals with variable fluid properties" (p. 1).
Date: July 1951
Creator: Deissler, Robert G.
Item Type: Refine your search to only Report
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An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors

Description: From Introduction: "As more quantitative information becomes available, more will be known of the maximum stage total-pressure ratios that can be used while maintaining acceptable efficiences and weight flows. Because quantitative knowledge is limited, the qualitative nature of limiting factors and trends are investigated herein."
Date: December 1951
Creator: Voit, Charles H. & Thomson, Arthur R.
Item Type: Refine your search to only Report
open access

Analytical method for determining performance of turbojet-engine tail-pipe heat exchangers

Description: From Introduction: "The NACA Lewis laboratory has undertaken a program of analytical study to evaluate the effect on turbojet-engine performance of extracting energy from several points in the cycle. The program included an investigation of the effects of air bleed from the compressor outlet, hot gas bleed from the turbine inlet, hot gas bleed from the turbine outlet, and shaft power extraction (references 1 to 4). "
Date: September 1951
Creator: Behun, Michael & Chandler, Harrison C., Jr.
Item Type: Refine your search to only Report
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Applicability of the hypersonic similarity rule to pressure distributions which include the effects of rotation for bodies of revolution at zero angle of attack

Description: The analysis of Technical Note 2250, 1950, is extended to include the effects of flow rotation. It is found that the theoretical pressure distributions over drive cylinders can be related by the hypersonic similarity rule with sufficient accuracy for most engineering purposes. The error introduced into pressure distributions and drag effective cylinders by ignoring the rotation term in the characteristic equations is investigated.
Date: June 1951
Creator: Rossow, Vernon J.
Item Type: Refine your search to only Report
open access

Application of Response Function to Calculation of Flutter Characteristics of a Wing Carrying Concentrated Masses

Description: Note presenting concepts involved in the harmonic-response-function method, such as the direct or conjugate characteristic modes, by application of the method to the calculation of the change in flutter characteristics of a wing due to adding concentrated masses.
Date: November 1951
Creator: Serbin, H. & Costilow, E. L.
Item Type: Refine your search to only Report
open access

Application of the Von Kármán momentum theorem to turbulent boundary layers

Description: Report presenting a study of the Von Kármán momentum theorum with respect to its application to turbulent boundary layers in a positive pressure gradient. The results indicate that the streamwise derivative of the turbulent longitudinal momentum may be large near the separation and therefore should be considered when the momentum theorum is used for turbulent boundary layers near separation.
Date: December 1951
Creator: Bidwell, Jerold M.
Item Type: Refine your search to only Report
open access

Application of Variational Methods to Transonic Flows With Shock Waves

Description: Note presenting a modification of certain variational methods for the approximate solution of subsonic and transonic flows to compensate for the fact that those methods fail as soon as shock waves occur. By applying a variational principle to the regions of flow behind shock waves and Bateman's original principle to the other regions in the fluid, shock equations can be directly obtained.
Date: November 1951
Creator: Wang, Chi-Teh & Chou, Pei-Chi
Item Type: Refine your search to only Report
open access

Application of X-Ray Absorption to Measurement of Small Air-Density Gradients

Description: Report presenting an analysis of two x-ray absorption methods for determining small air-density gradients. One method uses a Geiger-Mueller counter for detection and the other uses photographic film for detection. Both of the methods are found to have some advantages and disadvantages.
Date: July 1951
Creator: Weltmann, Ruth N.; Fairweather, Steven & Papke, Daryl
Item Type: Refine your search to only Report
open access

Approximate Calculation of Turbulent Boundary-Layer Development in Compressible Flow

Description: Note presenting numerical solutions of quantities appearing in the Karman momentum equation for the development of a turbulent boundary layer in plane and in radial compressible flows along thermally insulted surfaces in tabular form for a rnage of Mach numbers from 0.100 to 10. Through use of the tables, approximate calculation of boundary-layer growth is reduced to routine arithmetic computation.
Date: April 1951
Creator: Tucker, Maurice
Item Type: Refine your search to only Report
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Approximate design method for high-solidity blade elements in compressors and turbines

Description: Note presenting an approximate blade-element design method for compressible or incompressible nonviscous flow in high-solidity stators or rotors of axial-, radial-, or mixed-flow compressors, turbines, or two-dimensional cascades. The method is based upon channel-type flow between blade elements on a specified surface of revolution that lies between the hub and shroud and is concentric with the axis of the compressor turbine.
Date: July 1951
Creator: Stanitz, John D.
Item Type: Refine your search to only Report
open access

Approximate methods for calculating the flow about nonlifting bodies of revolution at high supersonic airspeeds

Description: Explicit expressions are developed which yield the Mach number and pressure distributions on the surfaces of pointed nonlifting bodies of revolution operating at high supersonic airspeeds and at values of the hypersonic similarity parameter (ratio of free-stream Mach number to slenderness ratio) greater than 1. Very simple explicit expressions are obtained for these distributions in the special case of slender bodies. In the case of cones, the analytic solutions accurately define the entire flo… more
Date: December 1951
Creator: Eggers, A. J., Jr. & Savin, Raymond C.
Item Type: Refine your search to only Report
open access

Automatic control systems satisfying certain general criterions on transient behavior

Description: Report presenting an analytic method for the design of automatic controls that has been developed and starts from arbitrary criterions on the behavior of the controlled system and gives those physically realizable equations that the control system can follow in order to realize the behavior. The criterions used are developed in the form of certain time integrals. General results are shown for systems of second order and of any number of degrees of freedom.
Date: June 1951
Creator: Boksenbom, Aaron S. & Hood, Richard
Item Type: Refine your search to only Report
open access

Axial-Momentum Theory for Propellers in Compressible Flow

Description: Note presenting the development of the axial-momentum theory for compressible flow as a step in the formulation of a rational propeller theory for compressible flow. The simple theory neglects some properties but predicts flow conditions through a propeller that are significantly different from the conditions predicted by the incompressible-flow theory.
Date: July 1951
Creator: Vogeley, Arthur William
Item Type: Refine your search to only Report
open access

Bench-Test Investigation of the Transient-Response Characteristics of Several Simulated Airplanes Incorporating an Autopilot Sensitive to Yawing Accelerations

Description: Note presenting testing of an autopilot sensitive to yawing acceleration, which was used to control four simulated airplane (mass-spring) configurations, and a series of bench tests to determine the response characteristics of the combinations.
Date: July 1951
Creator: Howard, Donald A.
Item Type: Refine your search to only Report
open access

A biharmonic relaxation method for calculating thermal stress in cooled irregular cylinders

Description: Report presenting a numerical method for calculating thermal stresses in irregular cylinders cooled by one or more internal passages. The use of relaxation methods and elementary methods of finite differences was found to give approximations to correct values when compared with previously known solutions for concentric circular cylinders with symmetrical and asymmetrical temperature distributions.
Date: August 1951
Creator: Holms, Arthur G.
Item Type: Refine your search to only Report
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