UNT Libraries Government Documents Department - 390 Matching Results

Search Results

Results: 1 - 24 next
open access

Pulse Amplifiers Using Transistor Circuits

Description: From Introduction: "The high frequency response remains important even when pulse shaping is introduced. Pulse shaping is used to improve the time resolution of the system, to minimize overload distortion, or to facilitate the action of discriminating and recording circuits. The amplifier response may be optimized by such shaping, but in general the overall characteristics will be fixed by the particular detector system."
Date: January 23, 1958
Creator: Graveson, R. T. & Sadowski, H.
Item Type: Refine your search to only Report
open access

Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models

Description: Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each… more
Date: July 23, 1957
Creator: Smith, Willard G. & Intrieri, Peter F.
Item Type: Refine your search to only Report
open access

Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds

Description: Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.
Date: August 23, 1955
Creator: Neely, Robert H. & Griner, Roland F.
Item Type: Refine your search to only Report
open access

Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51

Description: Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date: June 23, 1958
Creator: Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
Item Type: Refine your search to only Report
open access

Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model

Description: Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.
Date: August 23, 1956
Creator: Paulson, John W. & Boisseau, Peter C.
Item Type: Refine your search to only Report
open access

Material Compatibility With Gaseous Fluorine

Description: Report presenting static tests on the compatibility of gaseous fluorine with various liquids, solid plastics, waxes, and greases at pressures of 0 and 1500 pounds per square inch gage and atmospheric temperature. Several materials were found to be compatible at atmospheric pressure, but only Teflon and ruby were compatible under static conditions at 1500 pounds per square inch gage.
Date: January 23, 1957
Creator: Price, Harold G., Jr. & Douglass, Howard W.
Item Type: Refine your search to only Report
open access

Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7

Description: Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.
Date: September 23, 1952
Creator: Chubb, Robert S.
Item Type: Refine your search to only Report
open access

Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control

Description: Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.
Date: August 23, 1957
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
open access

An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System

Description: Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible t… more
Date: November 23, 1956
Creator: Douvillier, Joseph G., Jr.; Foster, John V. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
open access

Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95

Description: Memorandum presenting the effect of blunting on the internal performance of a two-cone inlet with an internally cylindrical cowl investigated experimentally at Mach number 4.95. Total-pressure-recovery and mass-flow data were obtained for a range of spike and cowl bluntness.
Date: September 23, 1958
Creator: Weston, Kenneth C.
Item Type: Refine your search to only Report
open access

Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet

Description: Report presenting an investigation of the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in the supersonic wind tunnel. The investigation was carried out to determine the performance penalties associated with spike-tip and cowl-lip blunting. Results regarding the effect of rounding the spike tip on inlet performance, overall drag coefficients, flow distortion, and Schileren photographs are provided.
Date: September 23, 1958
Creator: Cubbison, R. W. & Samanich, N. E.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Boundary-Layer Suction Through Slots to Obtain Extensive Laminar Boundary Layers on a 15 Percent-Thick Airfoil Section at High Reynolds Numbers

Description: Memorandum presenting a two-dimensional wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and difficulties encountered in obtaining extensive laminar flow are provided.
Date: June 23, 1952
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Item Type: Refine your search to only Report
open access

Experimental Study of Isothermal Wake-Flow Characteristics of Various Flame-Holder Shapes

Description: "An investigation of the isothermal wake-flow characteristics of several flame-holder shapes was carried out in a 4- by 4-inch flow chamber. The effects of flame-holder-shape changes on the characteristics of the Karman vortices and thus on the recirculation zones to which experimenters have related the combustion process were obtained for several flame holders. The results may furnish a basis of correlation, of combustion efficiency and stability for similarly shaped flame holders in combustio… more
Date: January 23, 1952
Creator: Younger, George G.; Gabriel, David S. & Mickelsen, William R.
Item Type: Refine your search to only Report
open access

Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds

Description: Control trailing-edge thickness and aspect ratio effect on oscillating hinge-moment and flutter characteristics of flap-type controls. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date: April 23, 1958
Creator: Moseley, William C., Jr. & Thompson, Robert F.
Item Type: Refine your search to only Report
open access

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Description: "A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor" (p. 1).
Date: September 23, 1958
Creator: Nettles, J. Cary
Item Type: Refine your search to only Report
open access

Summary of NACA Research on Afterburners for Turbojet Engines

Description: Report presenting a summary of NACA research on afterburners for turbojet engines during the past 5 years. The references present over 1000 afterburner configurations and about 3500 hours of operation. The report covers the following topics: burner-inlet diffusers, fuel-injection systems, flameholders, combustion space, combustion instability, starting and transient performance, effects of diluents, and burner-shell cooling.
Date: March 23, 1956
Creator: Lundin, Bruce T.; Gabriel, David S. & Fleming, William A.
Item Type: Refine your search to only Report
open access

Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0

Description: "Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery f… more
Date: September 23, 1958
Creator: Anderson, Bernhard H. & Bowditch, David N.
Item Type: Refine your search to only Report
open access

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Description: "Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).
Date: July 23, 1957
Creator: Spahr, J. Richard & Polhamus, Edward C.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09

Description: Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.
Date: March 23, 1956
Creator: Carmel, Melvin M. & Gregory, Donald T.
Item Type: Refine your search to only Report
open access

Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations

Description: An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio r… more
Date: August 23, 1950
Creator: Jones, W. L.; Shillito, T. B. & Henzel, J. G., Jr.
Item Type: Refine your search to only Report
open access

Influence of tube-entrance configuration on average heat-transfer coefficients and friction factors for air flowing in an Inconel tube

Description: A heat-transfer investigation was conducted with air flowing through an electrically heated Inconel tube having either a long-approach or a right-angle-edge entrance, an inside diameter of 0.402 inch, and a length of 24 inches over a range of Reynolds numbers up to 375,000 and average inside-tube-wall temperatures up to 2000 degrees R. Good correlation of heat-transfer data was obtained for both entrances, which substantiates work previously reported. A fair correlation of friction data was obt… more
Date: August 23, 1950
Creator: Lowdermilk, Warren H. & Grele, Milton D.
Item Type: Refine your search to only Report
open access

Investigation of downwash and wake characteristics at a Mach number of 1.53 3: swept wings

Description: Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.
Date: February 23, 1950
Creator: Perkins, Edward W. & Canning, Thomas N.
Item Type: Refine your search to only Report
Back to Top of Screen