UNT Libraries Government Documents Department - 13,786 Matching Results

Search Results

prev Results: 13225 - 13248 next
open access

Estimation of Pressures on Cockpit Canopies, Gun Turrets, Blisters, and Similar Protuberances

Description: Report presenting methods for estimating pressure distributions over protuberances such as cockpit canopies, gun turrets, blisters, scoops, and sighting domes. The methods are applied to the estimation of the pressure distributions over spherical segment and faired gun turrets and over the protuberances on the Brewster SB2A-1 airplane. The effects of compressibility, interference, and flow separation are discussed.
Date: May 1944
Creator: Wright, Ray H.
Item Type: Refine your search to only Report
open access

Comparison of Two-Dimensional Air Flows About an NACA 0012 Airfoil of 1-Inch Chord at Zero Lift in Open and Closed 3-Inch Jets and Corrections for Jet-Boundary Interference

Description: Note presenting pressure distributions and schileren photographs for the high-speed flow about a symmetrical airfoil at zero lift in open and closed jets in order to show the nature of the jet-boundary interference. Results regarding the application of jet-boundary-interference theory, analysis of experimental wall-interference data and comparison with theory, conditions near choking, and change of velocity ratio with Mach number are provided.
Date: May 1946
Creator: Wright, Ray H. & Donaldson, Coleman duP.
Item Type: Refine your search to only Report
open access

Characteristics of a Transonic Test Section With Various Slot Shapes in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting a large wind tunnel that has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of a slotted wind tunnel has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality can be produced.
Date: October 18, 1951
Creator: Wright, Ray H. & Ritchie, Virgil S.
Item Type: Refine your search to only Report
open access

NACA Transonic Wind-Tunnel Test Sections

Description: Report presents an approximate subsonic theory for the solid-blockage interference in circular wind tunnels with walls slotted in the direction of flow. This theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date: June 20, 1955
Creator: Wright, Ray H. & Ward, Vernon G.
Item Type: Refine your search to only Report
open access

NACA Transonic Wing-Tunnel Test Sections

Description: Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date: October 25, 1948
Creator: Wright, Ray H. & Ward, Vernon G.
Item Type: Refine your search to only Report
open access

Characteristics of the Langley 8-Foot Transonic Tunnel With Slotted Test Section

Description: "A large wind tunnel, approximately 8 feet in diameter, has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of such a slotted wind tunnel, already known with respect to the reduction of the subsonic blockage interference and the production of continuously variable supersonic flows, has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality could be produced. Experimental l… more
Date: July 3, 1958
Creator: Wright, Ray H.; Ritchie, Virgil S. & Pearson, Albin O.
Item Type: Refine your search to only Report
open access

Formulas and Tables of Coefficients for Numerical Differentiation With Function Values Given at Unequally Spaced Points and Application to Solution of Partial Differential Equations

Description: Note presenting general differentiation formulas for successive derivative of a function, which are obtained in terms of the values of the function at unequally spaced arguments and the corresponding distances between the successive arguments using Lagrangian polynominals of various degrees. A general discussion of applying the formulas to the numerical solution of partial differential equations is made.
Date: November 1950
Creator: Wu, Chung-Hua
Item Type: Refine your search to only Report
open access

A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachines of Axial-, Radial-, and Mixed-Flow Types

Description: Note presenting a general theory of steady three-dimensional flow of a nonviscous fluid in subsonic and supersonic turbomachines with arbitrary hub and casing shapes and a finite number of blades. The equations obtained to describe the fluid flow on these stream surfaces show clearly the several approximations involved in ordinary two-dimensional treatments.
Date: January 1952
Creator: Wu, Chung-Hua
Item Type: Refine your search to only Report
open access

A General Through-Flow Theory of Fluid Flow With Subsonic or Supersonic Velocity in Turbomachines of Arbitrary Hub and Casing Shapes

Description: Note presenting a general steady through-flow theory of nonviscous fluid in turbomachines of arbitrary hub- and casing-wall shapes with subsonic or supersonic velocity. The theory is applicable to both direct and inverse problems and is derived primarily for use in turbomachines with thin blades of high solidity with a simple approximate correction factor for blade-thickness effect.
Date: March 1951
Creator: Wu, Chung-Hua
Item Type: Refine your search to only Report
open access

Matrix and Relaxation Solutions That Determine Subsonic Through Flow in an Axial-Flow Gas Turbine

Description: Note presenting a method recently developed for determining the steady flow of a nonviscous compressible fluid along a relative stream surface between adjacent blades in a turbomachine, which was applied to investigate the subsonic through flow in a single-stage axial-flow gas turbine. In all solutions considered in the investigation, convergence was obtained without difficulty. Results regarding incompressible solutions and compressible solutions are provided.
Date: July 1952
Creator: Wu, Chung-Hua
Item Type: Refine your search to only Report
open access

Subsonic Flow of Air Through a Single-Stage and a Seven-Stage Compressor

Description: Note presenting a method for solving the steady flow of a non-viscous compressible fluid along a relative stream surface between two adjacent blades in a turbomachine that is applied to investigate the low- and high-speed subsonic air flow through a single-stage and through a seven-stage axial compressor. Comparisons of the design, flow, and air compressibility are provided.
Date: June 1953
Creator: Wu, Chung-Hua
Item Type: Refine your search to only Report
open access

Survey of Available Information on Internal Flow Losses Through Axial Turbomachines

Description: "Due to the scattered nature of existing information on the losses involved in the internal flow of gases through axial compressors and turbines, a brief survey of the available information on such losses is made. The present state of knowledge and the direction of future research toward the reduction of these losses are indicated" (p. 1).
Date: January 26, 1951
Creator: Wu, Chung-Hua
Item Type: Refine your search to only Report
open access

Method of Analysis for Compressible Flow Arbitrary Turbomachine Blades on General Surface of Revolution

Description: Note presenting a method of obtaining the flow of a nonviscous compressible fluid past arbitrary compressor or turbine blades between two neighboring surfaces of revolution. Satisfactory results were obtained by the method described in the investigation of the detailed flow variation of a compressible fluid past typical high-solidity, highly cambered thick turbine blades on a cylindrical surface.
Date: July 1951
Creator: Wu, Chung-Hua & Brown, Curtis A.
Item Type: Refine your search to only Report
open access

A Method of Designing Turbomachine Blades With a Desirable Thickness Distribution for Compressible Flow Along an Arbitrary Stream Filament of Revolution

Description: Note presenting a rapid method for designing turbomachine blades of a given turning and a desirable blade-thickness distribution for a compressible non-viscous fluid flow along an arbitrary stream filament of revolution. The method is illustrated with the design of several turbine cascades of highly cambered thick blades.
Date: September 1951
Creator: Wu, Chung-Hua & Brown, Curtis A.
Item Type: Refine your search to only Report
open access

A method of solving the direct and inverse problem of supersonic flow along arbitrary stream filaments of revolution in turbomachines

Description: Report presenting an analysis of the supersonic flow in two two-dimensional high-solidity cascades and in a partly supersonic symmetrical nozzle. A method is developed for the determination of the supersonic flow along stream surfaces of revolution in turbomachines. In addition to their use in direct problems, the equations can be used to design blade elements in supersonic flow along an arbitrary stream filament of revolution in turbomachines.
Date: September 1951
Creator: Wu, Chung-Hua & Costilow, Eleanor L.
Item Type: Refine your search to only Report
open access

Application of Radial-Equilibrium Condition to Axial-Flow Compressor and Turbine Design

Description: Note presenting some of the basic general equations governing the three-dimensional compressible flow of gas through a compressor or a turbine in terms of velocity components, total enthalpy, and entropy. The equations are applied to investigate the maximum compatible number of the radial variations of the gas properties between successive blade rows that a designer is free to specify.
Date: January 1949
Creator: Wu, Chung-Hua & Wolfenstein, Lincoln
Item Type: Refine your search to only Report
open access

Application of Radial-Equilibrium Condition to Axial-Flow Compressor and Turbine Design

Description: "Basic general equations governing the three-dimensional compressible flow of gas through a compressor or turbine are given in terms of total enthalpy, entropy, and velocity components of the gas. Two methods of solution are obtained for the simplified, steady axially symmetric flow; one involves the use of a number of successive planes normal to the axis of the machine and short distances apart, and the other involves only three stations for a stage in which an appropriate radial-flow path is … more
Date: January 1, 1949
Creator: Wu, Chung-Hua & Wolfenstein, Lincoln
Item Type: Refine your search to only Report
open access

Analysis of flow in a subsonic mixed-flow impeller

Description: From Introduction: "A brief description of the method of analysis is presented herein considering the mean stream surface approach advanced in references 2 and 3, and both the incompressible and compressible solutions are given in detail."
Date: August 1952
Creator: Wu, Chung-Hua; Brown, Curtis A. & Costilow, Eleanor L.
Item Type: Refine your search to only Report
open access

An approximate method of determining the subsonic flow in an arbitrary stream filament of revolution cut by arbitrary turbomachine blades

Description: Report presenting a method to obtain a relatively quick approximate determination of the detailed subsonic flow of a nonviscous fluid past arbitrary turbomachine blades. The method is illustrated with examples of compressible flow in a turbine cascade and in a centrifugal compressor.
Date: June 1952
Creator: Wu, Chung-Hua; Brown, Curtis A. & Prian, Vasily D.
Item Type: Refine your search to only Report
open access

Theoretical effect of inlet hub-tip-radius ratio and design specific mass flow on design performance of axial-flow compressors

Description: Report presenting an analysis of the effect at design condition of inlet hub-tip-radius ratio and mass flow per unit frontal area on the allowable rotor-tip speed, pressure ratio, and power input per unit frontal area of multistage axial-flow compressors with approximately symmetrical velocity diagrams at all radii, constant total enthalpy along the radius, a maximum Mach number of 0.8 for all stages, and a prescribed empirical turning limitation. The analysis indicated that for any given hub-t… more
Date: April 1950
Creator: Wu, Chung-Hua; Sinnette, John T. & Forrette, Robert E.
Item Type: Refine your search to only Report
open access

Analysis of plane-plastic stress problems with axial symmetry in strain-hardening range

Description: From Introduction: "A simple method of solving plane-plastic-stress problems with axial symmetry in the strain-hardening range for finite strains were developed at the NACA Lewis laboratory during 1949-1950. This method is based on the deformation theory of Hencky and Nadai (references 7 to 9), which is derived for the condition of constant directions and ratios of the principal stresses during loading."
Date: 1951
Creator: Wu, M. H. Lee
Item Type: Refine your search to only Report
Back to Top of Screen