UNT Libraries Government Documents Department - 37 Matching Results

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Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale … more
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Item Type: Refine your search to only Report
open access

An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers From 3.0 to 6.3

Description: Memorandum presenting static longitudinal stability and control characteristics of a flare-stabilized body of revolution employing a movable portion of the flare surface as a pitch control determined for a range of Mach numbers, angles of attack, and control deflections. The variation of lift coefficient with pitching-moment coefficient for the basic configuration with control undeflected was found to be essentially linear, and the stability to increase slightly with increasing Mach number.
Date: June 24, 1958
Creator: Gloria, Hermilo R.
Item Type: Refine your search to only Report
open access

Influence of Alloying upon Grain-Boundary Creep

Description: "Grain-boundary displacement, occurring in bicrystals during creep at elevated temperature (350 degrees c), has been measured as a function of the copper content (0.1 to 3 percent) in a series of aluminum-rich aluminum-copper solid-solution alloys. The minimums in stress and temperature, below which grain-boundary motion does not occur, increase regularly with the copper content as would be expected if recovery is necessary for movement. Otherwise, the effects, if any, of the copper solute upon… more
Date: June 24, 1955
Creator: Rhines, F. N.; Bond, W. E. & Kissel, M. A.
Item Type: Refine your search to only Report
open access

Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data

Description: "A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could t… more
Date: June 24, 1958
Creator: Shanks, Robert E.
Item Type: Refine your search to only Report
open access

NACA Zero Power Reactor Facility Hazards Summary

Description: "The Lewis Flight Propulsion Laboratory of the National Advisory Committee for Aeronautics proposes to build a zero power research reactor facility which will be located in the laboratory grounds near Cleveland, Ohio. The purpose of this report is to inform the Advisory Committee on Reactor Safeguards of the U. S. Atomic Energy Commission in regard to the design of the reactor facility, the characteristics of the site, and the hazards of operation at this location. The purpose of this reactor i… more
Date: June 24, 1957
Creator: Lewis Laboratory Staff
Item Type: Refine your search to only Report
open access

Low-Amplitude Damping-in-Pitch Characteristics of Tailless Delta-Wing-Body Combinations at Mach Numbers From 0.80 to 1.35 as Obtained With Rocket-Powered Models

Description: Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.
Date: June 24, 1954
Creator: D'Aiutolo, Charles T.
Item Type: Refine your search to only Report
open access

Effects of Chord Discontinuities and Chordwise Fences on Low-Speed Static Longitudinal Stability of an Airplane Model Having a 35 Degree Sweptback Wing

Description: Report presenting the results of an investigation to determine the effect of chord discontinuities and chordwise fences on the static longitudinal stability and wake characteristics of an airplane model with a 35-degree sweptback wing. The use of a fence or chord extension was found to cause a slight improvement in the static longitudinal stability of the basic wing alone. The force data and flow characteristics in the form of wake surveys and surface tufts are provided.
Date: June 24, 1952
Creator: Jaquet, Byron M.
Item Type: Refine your search to only Report
open access

Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

Description: From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the … more
Date: June 24, 1952
Creator: Hammond, Alexander D. & McMullan, Barbara M.
Item Type: Refine your search to only Report
open access

Some stress rupture and creep properties of molybdenum disilicide in the range of 1600 to 2000 F

Description: Report presenting an investigation of the stress-rupture and creep properties of hot-pressed molybdenum disilicide, which explored the stress-rupture properties, use of molybdenum disilicide at various temperatures, long-time strength, and a satisfactory method for creep and stress-rupture testing.
Date: June 24, 1952
Creator: Maxwell, W. A.
Item Type: Refine your search to only Report
open access

Investigation of Effective Thermal Conductivities of Powders

Description: Memorandum presenting a simplified analysis to determine the effective thermal conductivity of a powder from the fraction of space occupied by the gas and conductivities of the solid and the gas which make up the powder. Tests were conducted to determine the conductivity of magnesium oxide powder in various gases at a range of temperatures. The effects of some of the factors neglected in the simplified analysis, such as bending of the heat-flow lines and the irregularity of the arrangement of t… more
Date: June 24, 1952
Creator: Deissler, R. G. & Eian, C. S.
Item Type: Refine your search to only Report
open access

Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-Inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93

Description: Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.
Date: June 24, 1954
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Drag Characteristics of a Fin Stabilized Body of Revolution With a Fineness Ratio of 12 as Measured by the Free-Fall Method

Description: Report presenting measurements of longitudinal stability and drag characteristics of a fin-stabilized body of revolution with a fineness ratio 12 at low angles of attack using the free-fall method. Information about the data obtained from testing as well as the experimental coefficients related to body normal-force, total longitudinal-force, and body moment with Mach number is provided.
Date: June 24, 1954
Creator: Kurbjun, Max C.
Item Type: Refine your search to only Report
open access

A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 3

Description: Report presenting free-falling recoverable-model tests at transonic speeds on a model with a triangular wing of aspect ratio 3 and a 45 degree swept tail located in the chord plane of the wing. Static and dynamic longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at a range of angles of attack. results regarding lift, drag, static longitudinal stability, dynamic lon… more
Date: June 24, 1955
Creator: White, Maurice D.
Item Type: Refine your search to only Report
open access

Effects of propeller-spinner juncture on the pressure-recovery characteristics of an NACA 1-series D-type cowl in combination with a four-blade single-rotation propeller at Mach numbers up to 0.83 and at an angle of attack of 0 degrees

Description: Report presenting an investigation to determine the effects of two types of propeller-spinner junctures on the pressure-recovery characteristics of an NACA 1-series D-type cowl with an NACA 1-series spinner, in combination with a four-blade single-rotation propeller.
Date: June 24, 1952
Creator: Sammonds, Robert I. & Molk, Ashley J.
Item Type: Refine your search to only Report
open access

Investigation at high subsonic speeds of the effect of adding various combinations of missiles on the aerodynamic characteristics of sweptback and unswept wings combined with a fuselage

Description: Report presenting an investigation at Mach numbers from 0.50 to 0.94 of the effects of two sizes of missiles in several combinations of spanwise and vertical positions on the aerodynamic characteristics of wing-fuselage combinations with a 46.7 degree sweptback wing and an essentially unswept wing. Results regarding the drag characteristics and lift and pitch characteristics are provided.
Date: June 24, 1954
Creator: Silvers, H. Norman & Alford, William J., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.
Date: June 24, 1958
Creator: Lord, Douglas R.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a 45 Degree Swept-Wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Item Type: Refine your search to only Report
open access

Some Effects of Mass Ratio on the Transonic Flutter Characteristics of Untapered 45 Degree Sweptback Wings of Aspect Ratios 2 and 3.5

Description: Report presenting a study of the effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5. A given wing at a given Mach number fluttered at essentially a fixed dynamic pressure regardless of the individual values of the fluid velocity and density. Results regarding the experimental data, analytical results, and a comparison of the two, are provided.
Date: June 24, 1958
Creator: Kelly, H. Neale
Item Type: Refine your search to only Report
open access

A study of the application of airfoil section data to the estimation of the high-subsonic-speed characteristics of swept wings

Description: Report presenting estimates of the variation with Mach number of the aerodynamic characteristics of swept wings on the basis of airfoil section data combined with span-loading theory. Results regarding adjusted wing theory procedure and adjusted wing data procedure are provided.
Date: June 24, 1955
Creator: Hunton, Lynn W.
Item Type: Refine your search to only Report
open access

THE ZIRFLEX PROCESS INTERIM DEVELOPMENT SUMMARY

Description: The Zircaloy-clad fuels and the application of the Zirflex Process for dissolution are discussed. Zirflex chemical flowsheets are presented as developed by pilot plant operatlons. The Zirflex Process is applicable to the reprocessing of fuels from the Dresden Reactor and the PWR Reactor. Other applications of the process are the Plutonium Recycle Test Reactor fuels and the New Production Reactor fuels, possible fuels from the Experimental Breeder Reactor; NPD-2 fuels; and fuels from Carolina-Vi… more
Date: June 24, 1959
Creator: Platt, A.M. & Cooley, C.R.
Item Type: Refine your search to only Report
open access

LECTURE NOTES ON REACTOR CONTROLS

Description: This material is the outgrowth of the notes prepared for lectures on reactor controls given in 1953-55 at the Oak Ridge School of Reactor Technology. The course on reactor controls was for the purpose of acquainting the student with some of the elementary considerations involved in setting up a control and safety system for a nuclear reactor. Topics are discussed on kinetics, neutron energies, poisoning, analog computing, instrumentation, start-up, neutron sources, etc. (W.D.M.)
Date: June 24, 1959
Creator: Walker, C S
Item Type: Refine your search to only Report
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