Technical Report Archive & Image Library (TRAIL) - 155 Matching Results

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Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades

Description: Report presenting an investigation of the stress distribution in the roots of the first three stages of the J6S axial-flow compressor in order to explain root failures experienced in service. Root failures were producible in the lab when high vibratory stresses were combined with simulated centrifugal loads. Results regarding fatigue tests on the original J6S blade roots and on two redesigned blade roots as well as a comparison of the different root designs are provided.
Date: September 8, 1955
Creator: Meyer, André J., Jr. & Kaufman, Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Initial Experiments on the Aerodynamic Cooling Associated With Large-Scale Vortical Motions in Supersonic Flow

Description: Report presenting a theory of reduction of convective heat transfer to a surface in supersonic flow by periodically imposing a large-scale vortical motion on the boundary layer and an experimental investigation of that theory. Results regarding the pulsating flow phenomena, heat-transfer characteristics, and aerodynamic characteristics are provided.
Date: March 8, 1955
Creator: Eggers, A. J., Jr. & Hermach, C. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic wind-tunnel investigation of the effects of external stores and store position on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane

Description: Report presenting an investigation in the transonic tunnel to determine the effects of adding external, pylon-suspended stores to a model of the Douglas D-558-II research airplane. Tests were made for two spanwise store locations and covered a range of angles of attack and Mach numbers. Results regarding the drag, lift, and pitching-moment characteristics are provided.
Date: November 8, 1955
Creator: Kelly, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Interaction of a Jet and Flat Plate Located in an Airstream

Description: Report presenting an evaluation of the interaction between a flat plate and a nearby jet issuing from a convergent nozzle over a range of pressure ratios and free-stream Mach numbers. The effect on the interaction of the presence of streamline, blunt-base, and curved-base fairings between the plate and parabolic afterbody housing the exit nozzle was also investigated.
Date: September 8, 1955
Creator: Englert, Gerald W.; Wasserbauer, Joseph F. & Whalen, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a high-solidity high-pressure-ratio transonic rotor

Description: A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.
Date: November 8, 1955
Creator: Neumann, Harvey E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at Supersonic Mach Numbers of an Automatic Acceleration Control Missile in Which Rate Damping Is Obtained From a Linear Accelerometer Placed Ahead of the Missile Center of Gravity

Description: Report presenting a supersonic flight investigation of a roll-stabilized acceleration control missile for a Mach number range from 1.4 to 1.7. The control system operation was found to be satisfactory and applicable to some present-day missiles using linear acceleration commands. Results regarding analysis, preflight simulator results, a comparison between simulator and analytical results, flight test results, and a comparison between the flight test and preflight simulator results are presente… more
Date: November 8, 1955
Creator: Seaberg, Ernest C.; Sproull, Royce H. & Reid, H. J. E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of leading-edge droop upon the pressure distribution and aerodynamic loading characteristics of a 45 degree sweptback wing at transonic speeds

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the chordwise pressure distributions, wing-panel characteristics, wing-section characteristics, and maximum additional normal load on wing leading edge are provided.
Date: November 8, 1955
Creator: Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers at positive and negative thrust at Mach numbers up to 0.90, including some aerodynamic characteristics of the NACA 4-(5)(05)-041 two- and four-blade, single-rotat

Description: Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.
Date: October 8, 1954
Creator: Walker, John H. & Reynolds, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 1: Compressor Design

Description: Memorandum presenting a five-stage axial-flow compressor with all rotor rows operating with transonic relative inlet Mach numbers designed as a research unit to study the potentialities and problems arising from the compounding of transonic stages. The report presents all design values and procedures, blade-row velocity diagrams, and the selection of blade shapes.
Date: September 8, 1954
Creator: Sandercock, Donald M.; Kovach, Karl & Lieblein, Seymour
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The origin and distribution of supersonic interference from measurement of individual forces on several wing-fuselage-store configurations 6: swept-wing heavy-bomber configuration with stores of different sizes and shapes

Description: Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. The separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. Results regarding drag, lift, pitching moment, side force, and yawing moment are provided.
Date: March 8, 1956
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A simulation study of a wingless missile

Description: Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.
Date: February 8, 1956
Creator: Lessing, Henry C. & Reese, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability Investigation for a Mach Number Range of 0.8 to 1.7 of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail

Description: Report presenting an investigation of an airplane configuration model with a 45 degree swept wing of aspect ratio 4.0 and a taper ratio 0.3 with a low swept horizontal tail to determine its longitudinal stability. Longitudinal aerodynamic coefficients and stability derivatives are presented as functions of Mach number over the test range. The results are compared to wind tunnel and rocket model data and generally show good agreement.
Date: February 8, 1956
Creator: McFall, John C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Free-Flight Study of the Drag and Stability of a Series of Short-Span Missiles at Mach Numbers From 0.9 to 1.3

Description: Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.
Date: February 8, 1956
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: Longitudinal Stability and Control of the D-558-1

Description: Report presenting the results of pitching-moment and lift measurements on a model of the D-558-1 airplane with no nose-inlet flow at several tail and elevator settings at a range of Mach numbers. Information about the stability, control, and downwash results is provided.
Date: July 8, 1948
Creator: Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ice protection of turbojet engines by inertia separation of water 2: single-offset-duct system

Description: Investigation of a single-offset-duct system designed to prevent entrance of water into a turbojet engine was conducted on a half-scale nacelle model. An investigation was made to determine ram-pressure recovery and radial velocity profiles at the compressor section and icing characteristics of such a duct system. At a design inlet velocity of 0.77, the maximum ram-pressure recovery attained with effective water-separating inlet was 77 percent, which is considerably less than attainable with a … more
Date: June 8, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ice protection of turbojet engines by inertia separation of water 3: annular submerged inlets

Description: Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at in… more
Date: June 8, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Internal-Film Cooling of Rocket Nozzles

Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous … more
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 2: aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

Description: Report presenting an experimental investigation to determine the aerodynamic load distributions of a series of five bodies with conical or slightly blunted noses and cylindrical afterbodies in the 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at Mach number 3.12 for a range of Reynolds numbers and angles of attack.
Date: May 8, 1952
Creator: Jack, John R. & Gould, Lawrence I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties

Description: Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.
Date: July 8, 1952
Creator: Black, John M. & Blomquist, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Forces and moments on pointed blunt-nosed bodies of revolution at Mach numbers from 2.75 to 5.00

Description: Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles of attack from 0 degrees to 25 degrees are presented and compared with theory. Cones and ogives of fineness ratios 3 to 7 and two blunt-nosed body shapes with fineness ratios 3 and 5 were tested at Mach numbers from 2.75 to 5.00. Reynolds numbers were from 0.5 million to 6.4 million, depending on Mach number and body fineness ratio.
Date: August 8, 1952
Creator: Dennis, David H. & Cunningham, Bernard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of internal configuration on afterburner shell temperatures

Description: From Summary: "A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance."
Date: January 8, 1952
Creator: Conrad, E. William & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Damping in Roll of Rocket-Powered Test Vehicles Having Swept, Tapered Wings of Low Aspect Ratio

Description: "Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the on… more
Date: October 8, 1951
Creator: Sanders, E. Claude, Jr. & Edmondson, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades

Description: From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mou… more
Date: September 8, 1952
Creator: Esgar, Jack B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation

Description: Report presenting a study of the supersonic longitudinal stability and control characteristics of a canard missile configuration using flight tests and wind-tunnel tests at a range of Mach numbers and Reynolds numbers. Good correlation was noted for the two techniques for slopes of lift and moment coefficients against angle of attack and for aerodynamic-center location.
Date: August 8, 1952
Creator: Curfman, Howard J., Jr. & Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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