UNT Libraries Government Documents Department - 819 Matching Results

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Reciprocity relations in aerodynamics

Description: From Introduction: "The purpose of the present paper is twofold. First, a close connection will be established between reverse-flow theorems in subsonic and supersonic, steady-state wing theory and known reciprocity relations between two solutions of the equation the flow field."
Date: May 1952
Creator: Heaslet, Max A. & Spreiter, John R.
Item Type: Refine your search to only Report
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A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees

Description: Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are… more
Date: October 30, 1952
Creator: Cooper, Morton; Gapcynski, John P. & Hasel, Lowell E.
Item Type: Refine your search to only Report
open access

The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow

Description: Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date: November 12, 1952
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
open access

Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel

Description: Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date: December 19, 1952
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
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Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

Description: A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made by means of a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and the outer-race bearing operating temperatures are computed for the laboratory test rig and the turbojet engine. A method is given that enables the designer… more
Date: 1952
Creator: Macks, E. Fred & Nemeth, Zolton N.
Item Type: Refine your search to only Report
open access

Experimental investigation of free-convection heat transfer in vertical tube at large Grashof numbers

Description: Report presents the results of an investigation conducted to study free-convection heat transfer in a stationary vertical tube closed at the bottom. The walls of the tube were heated, and heated air in the tube was continuously replaced by fresh cool air at the top. The tube was designed to provide a gravitational field with Grashof numbers of a magnitude comparable with those generated by the centrifugal field in rotating-blade coolant passages (10(8) to 10(13)). Local heat-transfer coefficien… more
Date: June 30, 1952
Creator: Eckert, E. R. G. & Diaguila, A. J.
Item Type: Refine your search to only Report
open access

A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound

Description: "Comparisons have been made of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution having the same axial developments of cross-sectional areas normal to the airstream. On the basis of these comparisons, it is concluded that near the speed of sound the zero-lift drag rise of a low-aspect-ratio thin-wing and body combination is primarily dependent on the axial development of the cross-sectional areas normal to the … more
Date: August 1, 1952
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
open access

The dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Description: From Summary: "The longitudinal and lateral-directional dynamic-response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements are presented and compared with predictions based on theoretical studies and wind-tunnel data. Flights were made at an altitude of 35,000 feet covering the Mach number range of 0.50 to 1.04. A limited amount of lateral-directional data were also obtained at 10,000 feet. The flight consisted essentially of recording transient… more
Date: September 17, 1952
Creator: Triplett, William C.; Brown, Stuart C. & Smith, G. Allan
Item Type: Refine your search to only Report
open access

Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From

Description: "An investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane has been conducted at Mach numbers from 0.6 to 1.5 by the Langley Pilotless Aircraft Research Division by utilizing rocket-propelled test vehicles. No effects of mutual interference between the midspan spoiler and the outboard aileron were detectable. Above the speed of sound, the ailerons were relatively ineffective as compared with the spoiler because of wing twisting" (p. 1).
Date: February 25, 1952
Creator: Strass, H. Kurt & Marley, Edward T.
Item Type: Refine your search to only Report
open access

Investigation of Statistical Nature of Fatigue Properties

Description: Note presenting an experimental program to study the subject of metal fatigue and to determine and evaluate the fundamental factors which influence the behavior. The statistics of the fatigue-fracture curves and endurance limits were determined for a variety of metals and the effects of some metallurgical factors on the statistical nature of fatigue properties were shown.
Date: June 1952
Creator: Epremian, E. & Mehl, R. F.
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

Calculations on the forces and moments for an oscillating wing-aileron combination in two-dimensional potential flow at sonic speed

Description: Report presenting the use of linearized theory for compressible unsteady flow to obtain the velocity potential and lift and moment for a thin, harmonically oscillating, two-dimensional wing-aileron combination moving at sonic speed.
Date: January 1952
Creator: Nelson, Herbert C. & Berman, Julian H.
Item Type: Refine your search to only Report
open access

The effects of Reynolds number on the application of NACA 16-series airfoil characteristics to propeller design

Description: Report presenting an analysis of airfoil data from several NACA 16-series propeller airfoils from tests of 5-inch chord models in the 24-inch high-speed tunnel and 12-inch-chord models in the 8-foot high-speed tunnel. Results indicated that differences of less than 1 percent in propeller efficiency at or near the design condition will be involved in applying data from 5-inch-chord and 12-inch-chord airfoil tests to full-scale propeller design.
Date: January 1952
Creator: Cleary, Harold E.
Item Type: Refine your search to only Report
open access

Orientation of orifices on bodies of revolution for determination of stream static pressure at supersonic speeds

Description: Report presenting experimental data obtained in the 4- by 4-foot supersonic tunnel for a parabolic body of revolution of large fineness ratio at mach number 1.59, which are analyzed in order to locate positions at which static-pressure orifices will indicate a constant static pressure independent of the pitch-yaw attitude of the body.
Date: January 1952
Creator: Cooper, Morton & Hamilton, Clyde V.
Item Type: Refine your search to only Report
open access

Design of two-dimensional channels with prescribed velocity distribution along the channel walls 1: relaxation solutions

Description: Report presenting a general method of design is developed for two-dimensional unbranched channels with prescribed velocities as a function of arc length along the channel walls. The method is developed for both incompressible and compressible, irrational, nonviscous flow. Five numerical examples are given including three elbow designs with the same prescribed velocity as a function of arc length along the channel walls but with incompressible, linearized compressible, and compressible flow.
Date: January 1952
Creator: Stanitz, John D.
Item Type: Refine your search to only Report
open access

An Impulse-Momentum Method for Calculating Landing-Gear Contact Conditions in Eccentric Landings

Description: "An impulse-momentum method for determining impact conditions for landing gears in eccentric landings is presented. The analysis is primarily concerned with the determination of contact velocities for impacts subsequent to initial touchdown in eccentric landings and with the determination of the effective mass acting on each landing gear. These parameters determine the energy-absorption requirements for the landing gear and, in conjunction with the particular characteristics of the landing gear… more
Date: January 1952
Creator: Yntema, Robert T. & Milwitzky, Benjamin
Item Type: Refine your search to only Report
open access

Investigation of Laminar Boundary Layer in Compressible Fluids Using the Crocco Method

Description: Note presenting the use of the Crocco method to solve the simultaneous differential equations of momentum and energy involved in the flow of air in a thin laminar boundary layer on a flat plate. The Crocco method was used because it gave accurate results for arbitrary Prandtl number near unity. Variations of shear, velocity, temperature, and Mach number across the boundary layer are included.
Date: January 1952
Creator: Van Driest, E. R.
Item Type: Refine your search to only Report
open access

Coincidence Method Applied to Ion Beam Measurement

Description: "A coincidence Geiger counter system was constructed for the absolute measurement of the activity of radioactive substances made in a cyclotron. The average beam current in the cyclotron can be calculated from the number of disintegrations per second observed, the half-life of the radioactive substance, and the reaction cross section" (p. 1).
Date: February 1952
Creator: Fultz, Stanley & Pool, M. L.
Item Type: Refine your search to only Report
open access

Numerical determination of indicial lift and moment functions for a two-dimensional sinking and pitching airfoil at Mach numbers 0.5 and 0.6

Description: Report presenting the indical lift and moment functions for sinking and pitching motion at Mach numbers 0.5 and 0.6. The functions are determined from a knowledge of existing oscillatory coefficients at low reduced frequencies and from approximate expressions of the coefficients at high reduced frequencies. Results regarding determination of indical functions, considerations for indical lift due to penetration of a sharp-edge gust, and approximation of indical functions by analytic expressions … more
Date: July 1952
Creator: Mazelsky, Bernard & Drischler, Joseph A.
Item Type: Refine your search to only Report
open access

Langley full-scale-tunnel investigations of the maximum-lift and stalling characteristics of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections

Description: Report presenting an investigation of the results at high Reynolds numbers and low Mach numbers to determine the maximum-lift and stalling characteristics of an aspect-ratio-4 trapezoidal wing with 10-percent-thick, circular-arc airfoil sections. Testing occurred measurements of lift, drag, and pitching-moment coefficients of the basic wing and of the wing with 0.20-chord droop-nose and rear flaps deflected alone and in combination with one another.
Date: November 1952
Creator: Lange, Roy H.
Item Type: Refine your search to only Report
open access

Some dynamic effects of fuel motion in simplified model tip tanks on suddenly excited bending oscillations

Description: Report presenting an exploratory investigation of the dynamic effects of fuel sloshing in tip tanks on suddenly excited bending oscillations using two simplified model beam-tank systems. Several fluids of different densities and viscosities were used in combination with various conditions of tank fullness. Results regarding the large and small beam-tank system are provided.
Date: September 1952
Creator: Merten, Kenneth F. & Stephenson, Bertrand H.
Item Type: Refine your search to only Report
open access

flow studies in the vicinity of a modified flat-plate rectangular wing of aspect ratio 0.25

Description: Report presenting an investigation in order to study the characteristics of flow in the vicinity of a rectangular wing of aspect ratio 0.25 with a modified flat-plate airfoil section. The investigation was conducted using photographs of a tuft grid located at a number of chordwise positions along the airfoil and behind the trailing edge. Results regarding the force-tests, formation of vortices and vorticity distribution in the wake, location of vortex cores, and chordwise growth of lift are pro… more
Date: September 1952
Creator: Michael, William H., Jr.
Item Type: Refine your search to only Report
open access

Bonding of molybdenum disulfide to various materials to form a solid lubricating film 1: the bonding mechanism

Description: Report presenting the use of molybdenum disulfide as a solid film lubricant in applications where designs or temperatures preclude liquid lubricants is dependent on successful bonding of the powder to the surface to be lubricated. An investigation was conducted to determine the basic mechanism of bonding and to extend application of the bonding to a variety of materials. Results regarding an examination of electron diffraction of MoS2 dusted and rubbed on steel, adherence of dry powders to meta… more
Date: February 1952
Creator: Godfrey, Douglas & Bisson, Edmond E.
Item Type: Refine your search to only Report
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