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An investigation of high-frequency combustion oscillations in liquid-propellant rocket engines

Description: From Summary: "An experimental investigation of high-frequency combustion oscillations (screaming) was conducted with a 100-pound-thrust acid-hydrocarbon rocket engine and a 500-pound-thrust oxygen-fuel rocket engine. The oscillation frequencies could be correlated as a linear function of the parameter C/L, where C is the experimentally measured characteristic velocity and L is the combustion-chamber length. The tendency of the engines to scream increased as chamber length was increased. With e… more
Date: June 26, 1953
Creator: Tischler, Adelbert O.; Massa, Rudolph V. & Mantler, Raymond L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wind-Tunnel Investigation of Store and Horizontal-Tail Loads and Some Effects of Fuselage-Afterbody Modifications on a Swept-Wing Fighter Airplane

Description: Report presenting an investigation of a swept-wing fighter airplane in the transonic tunnel to determine store and pylon loads and the effect of store installation of drag and stability, horizontal-tail loads at sideslip angles of 0 degrees and 5 degrees, and the extent of drag-rise reductions possible by enlarging the fuselage afterbody. Results regarding store and pylon installation, horizontal-tail characteristics, and effects of "area-rule" modifications are provided.
Date: April 10, 1956
Creator: Hallissy, Joseph M., Jr. & Kudlacik, Louis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Oak Ridge National Laboratory Research Reactor Safeguard Report

Description: The proposed ORNL Research Reactor is designed to serve as a general purpose research tool delivering a maximum thermal flux of 8x10^13 n/cm2-sec at the initial power level of five megawatts. Operation at power levels up to ten megawatts is proposed for such items as sufficient cooling capacity is available to handle the increased heat load. The reactor will use MTR-type fuel elements and beryllium reflector pieces in a 7 x 9 grid with moderation and cooling provided by forced circulation of de… more
Date: October 7, 1954
Creator: Binford, F. T.; Cole, T. E. & Gill, J. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: "Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).
Date: February 11, 1955
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Longitudinal Characteristics of the X-3 Configuration Using Rocket-Propelled Models: Preliminary Results at Mach Numbers From 0.65 to 1.25

Description: Report presenting a rocket-powered model of the X-3 configuration flown through a range of Mach numbers to determine the response of the model to rapid deflections of the horizontal tail and its effects on lift, drag, longitudinal stability and control, and longitudinal-trim change. The model was found to remain statically and dynamically stable through the lift-coefficient and Mach number range of the test.
Date: December 1, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effects of Changes in Aspect Ratio and Tail Height on the Longitudinal Stability Characteristics at High Subsonic Speeds of a Model With a Wing Having 32.6 Degree Sweepback

Description: Report discussing an investigation to determine the effects of changes in aspect ratio and tail height on the longitudinal stability characteristics of a model with a 32.6-degree sweptback wing. The effects of a leading-edge discontinuity were also examined.
Date: February 2, 1954
Creator: Alford, William J., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop

Description: Report presenting an investigation in the 16-foot and 8-foot transonic tunnel to determine the effects of Reynolds number and on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, 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 effect of Reynolds number on the aerodynamic characteristics and effects of roughness strips are provided.
Date: February 4, 1955
Creator: Schmeer, James W. & Cooper, J. Lawrence
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing of the Northrop MX-775A Missile With Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.
Date: February 11, 1955
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigations of the damping in roll of swept and tapered wings at supersonic speeds

Description: Report presenting experimental damping-in-roll derivatives obtained for a series of 33 swept and tapered wings. The wing plan forms were selected so that a range of leading-edge positions ahead of and behind the Mach cone obtained at three Mach numbers.
Date: March 3, 1953
Creator: McDearmon, Russell W. & Heinke, Harry S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of the effects of various underwing external-store arrangements on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II Research Airplane

Description: Report presenting an investigation at high subsonic speeds of various arrangements of underwing external stores on a model of the Douglas D-558-II research airplane. Three sizes of a short-cylinder shape and two sizes of a long-cylinder shape were investigated with three thicknesses of pylon support on one store configuration. Results regarding drag characteristics and lift and pitch characteristics are provided.
Date: July 18, 1955
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of a Family of Diffusers Designed for Near Sonic Inlet Velocities

Description: Note presenting tests conducted with a series of diffuser shapes defined by empirical equations with constants which are related to the initial boundary-layer thickness. The shapes were designed to provide high pressure recovery at near sonic inlet Mach numbers, and tests were conducted through the mass-flow range with a variety of attached and separated initial boundary layers. Results regarding axially symmetric ducts with attached initial boundary layers, axially symmetric ducts with separat… more
Date: February 1956
Creator: Scherrer, Richard & Anderson, Warren E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Investigation of Effects of Spanwise and Chordwise External Store Location and Body Contouring on Aerodynamic Characteristics of 45 Degree Sweptback Wing-Body Configuration

Description: Report presenting an investigation to determine the effects of spanwise and chordwise external store location on the aerodynamic characteristics of a cambered 45 degree sweptback wing-body configuration at a range of Mach numbers. Information about the drag characteristics of the various configurations, lift characteristics, and longitudinal stability characteristics is presented.
Date: September 25, 1957
Creator: Pearson, Albin O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads

Description: Report presenting an investigation to determine the effects of location of bodies (finned and unfinned) on the aerodynamic characteristics of unswept- and swept-wing--fuselage models and to determine the aerodynamic loads on the bodies in the presence of the wings. Results for the complete model characteristics and for the body are provided.
Date: April 1, 1954
Creator: Alford, William J., Jr. & Silvers, H. Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Reflection of Weak Shock Wave From a Boundary Layer Along a Flat Plate 2: Interaction of Oblique Shock Wave With a Laminar Boundary Layer Analyzed by Differential-Equation Method

Description: Note presenting an investigation of the interaction of an oblique shock with a laminar boundary layer in a compressible supersonic stream. This report is a complement to previous report and uses the differential equation method.
Date: January 1953
Creator: Kuo, Yung-Huai
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An evaluation of non-Newtonian flow in pipe lines

Description: Report presenting an analysis of a method for determining pressure losses due to the flow of non-Newtonian materials in pipe lines by using basic flow data obtained from measurements of flow curves, which are rate-of-shear-shear-stress curves. Reported flow and pressure data are analyzed. The validity of the generalized friction diagram for describing flow of Bingham plastics in pipe lines is shown by an evaluation of experimental data of two independent investigators.
Date: February 1955
Creator: Weltmann, Ruth N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of a wing-propeller configuration employing large-chord plain flaps and large-diameter propellers for low-speed flight and vertical take-off

Description: Report presenting an investigation of the effectiveness of a wing equipped with large-chord plain flaps and auxiliary vanes in rotating the thrust vector of two large-diameter propellers through the large angles required for vertical take off and low-speed flight. The semispan model was equipped with a 60-percent-chord flap, a 30-percent-chord flap, and two large-diameter overlapping propellers. Results regarding static thrust conditions, tests with forward speed, and application of results are… more
Date: December 1954
Creator: Kuhn, Richard E. & Draper, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of longitudinal stability and control characteristics from free-flight model tests with results at transonic speeds for three airplane configurations

Description: From Summary: "A test technique and data analysis method has been developed for determining the longitudinal aerodynamic characteristics from free-flight tests of rocket-propelled models. The technique makes use of accelerometers and an angle-of-attack indicator to permit instantaneous measurements of lift, drag, and pitching moments. The data, obtained during transient oscillations resulting from control-surface disturbances, are analyzed by essentially nonlinear direct methods (such as cross … more
Date: 1957
Creator: Gillis, Clarence L. & Mitchell, Jesse L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

SM-1 Research and Development Program, Activity Buildup Program Task 1 : final report February 1958 to June 1959

Description: Abstract: The results of activity buildup studies in the SM-1 (APPR-1) performed from February 1958 to January 1959 are reported. Data are presented on the extent, nature, and mechanism of the buildup of long-lived gamma emitting nuclides in the reactor primary system. Mathematical equations to describe the activity buildup are derived. Radiation levels after reactor shutdown are presented, as well as the predicted radiation levels at the end of core life.
Date: August 10, 1959
Creator: Brown, William S.; Bergen, C. Richard.; Bergmann, Carl A.; Chupak, Julius.; Fitzsimmons, Susanne R. & Grant, Louis G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Description: At the request of the Bureau of Aeronautics, Department of the Navy, National Advisory Committee for Aeronautics has conducted a preliminary investigation at high subsonic speeds of the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane. The tests covered a Mach number range from 0.5 to 0.94 and corresponding Reynolds numbers, based on the wing mean aerodynamic chord, from 3.3 x 10(exp 6) to 4.3 x 10(exp 6). The maxi… more
Date: January 18, 1954
Creator: Spreemann, Kenneth P. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Aerodynamic Forces on Slender Plane- and Cruciform-Wing and Body Combinations

Description: From Introduction: "Since these results were not applicable to the present problem, a theoretical analysis of the aerodynamic properties of slender wing-body combinations was undertaken. The results of this investigation were first reported in reference 5 and were later extended in reference 6 to include cruciform-wing and body combinations. The present report summarizes and extends the theory and results previously presented in these references."
Date: 1950%
Creator: Spreiter, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static Longitudinal Stability and Control Characteristics of a 1/16 -Scale Model of the Douglas D-558-II Research Airplane at Mach Numbers of 1.61 and 2.01

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the static longitudinal stability and control characteristics of a 1/16-scale model of the Douglas D-558-II research airplane. The results indicated a high degree of longitudinal stability that decreased slightly with increasing Mach number and lift coefficient.
Date: November 6, 1953
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparative Costs Of Sea Disposal And Land Burial For The Radioactive Wastes Of The Lawrence Radiation Laboratory

Description: This report is a comparative cost study of radioactive waste disposal for the Lawrence Radiation Laboratory (UCRL). In particular, it compares the costs of sea disposal in depths of 1000 fathoms and of 2000 fathoms off the California coast with land burial of the wastes at the Hanford Atomic Products Operation (HAPO), Richland, Washington, at the National Reactor Testing Station (NRTS), Idaho Falls, Idaho, or at the Nevada Test Site (NTS), Nevada. In the comparison, the cost of utilizing a comm… more
Date: January 21, 1959
Creator: Nielsen, Elmer
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effects of Leading-Edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers From 0.40 to 0.93 of a Wing-Fuselage Configuration With a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Report presenting an investigation to determine the effects of a number of leading-edge flaps on the aerodynamic characteristics in pitch of a wing-fuselage configuration with a 45 degree sweptback wing. All of the flaps were found to reduce the drag in the medium lift range , but there were no significantly large effects on the lift characteristics for any of the arrangements studied.
Date: August 20, 1953
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Description: Report presenting a wind-tunnel investigation of the effects of fixing boundary-layer transition with wires on the aerodynamic characteristics of a wing-body configuration at a range of Mach numbers. The model consisted of an aspect-ratio-3 trapezoidal wing with a 3-percent-thick biconvex section in combination with a Sears-Haack body of revolution. Results regarding lift characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: July 1958
Creator: Hunton, Lynn W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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