Serial/Series Title
Country
States
1,171 Matching Results
Results open in a new window/tab.
Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation
Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.
Date:
January 20, 1958
Creator:
Turner, Horward L.; Rathert, George A., Jr. & Heinle, Donovan R.
System:
The UNT Digital Library
Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers
Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.
Date:
January 19, 1955
Creator:
Cavicchi, Richard H. & Constantine, Anita B.
System:
The UNT Digital Library
A Study of Injection Processes for 15-percent Fluorine-85- Percent Oxygen and Heptane in a 200-pound-thrust Rocket Engine
Injection techniques for fluorine, oxygen, and heptane in 200-pound thrust rocket engine.
Date:
January 15, 1957
Creator:
Heidmann, M. F.
System:
The UNT Digital Library
Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle
Report discussing an investigation of the effect of curved speed brakes on the drag characteristics and longitudinal stability and control characteristics of a model of the MX-1554A with a circular jet nozzle. The speed brakes were tested at several deflections, gaps, and locations in the landing configuration and clean configuration. Results of a lateral- and directional-stability study due to reduction in the vertical tail area are also provided.
Date:
January 7, 1954
Creator:
Solomon, Martin
System:
The UNT Digital Library
Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.
Date:
January 13, 1958
Creator:
Healy, Frederick M.
System:
The UNT Digital Library
Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01
"A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger" (p. 1).
Date:
January 15, 1957
Creator:
Kouyoumjian, Walter L.
System:
The UNT Digital Library
An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion
Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
Date:
January 19, 1953
Creator:
Karp, Irving M.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control
Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.
Date:
January 12, 1953
Creator:
Smith, Willard G.
System:
The UNT Digital Library
Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight
Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are provided.
Date:
January 18, 1955
Creator:
Eggers, A. J., Jr. & Syvertson, Clarence A.
System:
The UNT Digital Library
Material Compatibility With Gaseous Fluorine
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.
System:
The UNT Digital Library
Static Lateral-Directional Stability Characteristics of Five Contemporary Airplane Models From Wind-Tunnel Tests at High Subsonic and Supersonic Speeds
Memorandum presenting the static lateral-directional stability characteristics of several airplane models recently investigated which cover many of the geometric arrangements of high-speed airplane components of current interest. The results are limited to the most pertinent aerodynamic phenomena contributing to the lateral-directional characteristics of each airplane type. Results for five different models are provided.
Date:
January 4, 1956
Creator:
Smith, Willard G. & Ball, Louis H.
System:
The UNT Digital Library
Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06
Memorandum presenting an investigation to determine the drag, longitudinal stability, and lateral stability characteristics of a model of a fighter-type airplane. Several modifications were made to the model in an attempt to eliminate pitch-up.
Date:
January 18, 1957
Creator:
Carmel, Melvin M. & Turner, Kenneth L.
System:
The UNT Digital Library
Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane
Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.
Date:
January 24, 1958
Creator:
Sellers, Thomas B.
System:
The UNT Digital Library
Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6
Memorandum presenting forces and moments measured at Mach number 1.6 in the 4- by 4-foot supersonic pressure tunnel on bombs of fineness ratios 7.0 and 10.5 in the presence of a swept-wing fighter-bomber airplane configuration for a large number of positions under the fuselage. The results can be used to calculate bomb-drop paths.
Date:
January 31, 1957
Creator:
Geier, Douglas J. & Carlson, Harry W.
System:
The UNT Digital Library
Design charts for cross-flow tubular intercoolers charge-across-tube type
Report presenting equations relating the various dimensions, air mass flow, and performance of a cross-flow tubular intercooler in which the charge flows across and the cooling air through the tubes. Design charts are presented from which the intercooler design characteristics and performance can be quickly determined.
Date:
January 1941
Creator:
Reuter, J. George & Valerino, Michael F.
System:
The UNT Digital Library
An Investigation of Cowl-Flap and Cowl-Outlet Designs for the Boeing B-29 Power-Plant Installation
Report discussing an investigation into cowl-flap and cowl-outlet designs for the B-29 in order to determine the effects of cowling performance of different types of flaps and elements of flaps. Details of the available pressure drop and cooling-air pressure-drop distribution are also provided.
Date:
January 1946
Creator:
Wyatt, DeMarquis D. & Conrad, E. William
System:
The UNT Digital Library
Effect of Drawbar Upstream Location on Air Velocity Distribution at the Inlet Face of Reactor Segment Designed by the General Electric Company
The results of flow tests on a drawbar for the General Electric reactor segment test in the MTR are reported. The drawbar is a T-shaped obstruction located as close to the upstream face of the reactor test segment as possible without serious flow distortion ; the drawbar is required for instrumentation leads and segment insertion and removal in the MTR. The effect of drawbar upstream distance on velocity distribution across the segment face is evaluated for several Reynolds numbers.
Date:
January 1953
Creator:
Nagey, T. F. & Sams, E. W.
System:
The UNT Digital Library
The significance of the time concept in engine detonation
Report presenting an experimental technique developed by means of which the variables affecting the time element in the detonation process in a spark-ignition engine can be controlled and approximately measured. Results indicated that higher maximum permissible pressures can be used if the rate of compression of the end gas is increased. Suggestions for future study are provided.
Date:
January 1943
Creator:
Leary, W. A. & Taylor, E. S.
System:
The UNT Digital Library
Low-Speed Static Stability Characteristics of a Complete Model with an M-Wing in Mid and High Positions and with Three Horizontal-Tail Heights
Report presenting an investigation of the low-speed static longitudinal and lateral stability characteristics of a model with an M-wing in mid and high positions and with three horizontal-tail heights. The wing had its sweep discontinuity at 40-percent wing semispan, an aspect ratio of 6, a taper ratio of 0.60, NACA 65A009 airfoil sections parallel to the plane of symmetry, and 45 degrees sweep of the quarter-chord lines. Results regarding longitudinal stability characteristics and lateral stability characteristics are provided.
Date:
January 24, 1956
Creator:
Fournier, Paul G.
System:
The UNT Digital Library
Ground-Stand Cooling Investigation of an R-2600-22 Engine in a PBM-3D Nacelle
Report discussing an investigation of the cooling characteristics of an R-2600-22 engine installed in a PBM-3D nacelle. The investigation explored the general cooling characteristics by the NACA cooling-correlation method and an investigation of specific points on the engine cylinder where cooling was critical, including the exhaust-valve-crown and number 3 cylinder.
Date:
January 1946
Creator:
Spencer, Robert C.; Petring, F. William & Prince, William R.
System:
The UNT Digital Library
Investigation of a Cermet Gas-Turbine-Blade Material of Titanium Carbide Infiltrated With Hastalloy C
A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.
Date:
January 24, 1955
Creator:
Hoffman, Charles A.
System:
The UNT Digital Library
Initial inclination of the mixing boundary separating an exhausting supersonic jet from a supersonic ambient stream
Report presenting calculations of the initial inclination of the mixing boundary separating an exhausting supersonic jet from an external supersonic stream as a function of jet static-pressure ratio.
Date:
January 11, 1956
Creator:
Love, Eugene S.
System:
The UNT Digital Library
A Method for Studying the Transient Blade-Flapping Behavior of Lifting Rotors at Extreme Operating Conditions
Note presenting a method for studying the transient behavior of the flapping motion, as well as for calculating the steady-state flapping amplitudes, of free-to-cone and seesaw rotors operating at extreme flight conditions. The method is general and can be applied to blades of any airfoil section, mass distribution, twist, plan-form taper, root cutout, and flapping-hinge geometry.
Date:
January 1955
Creator:
Gessow, Alfred & Crim, Almer D.
System:
The UNT Digital Library
A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachines of Axial-, Radial-, and Mixed-Flow Types
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
System:
The UNT Digital Library