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Final Report: Airborne Reconnaissance Project Dripping Spring, Quartzite, Gila County, Arizona

Description: Abstract: A low-level airborne radiometric survey of the younger pre-Cambrian Dripping Spring quartzite, undertaken in the mountainous region lying roughly 100 riles east of Phoenix, was completed June 3, 1955. Twenty-seven radioactive anomalies were located. To date seven of these have produced uranium ore, four more will probably become producers, and six others may possibly become producers. Flying was concentrated in the Dripping Spring quartzite, but reconnaissance flights were made over o… more
Date: September 7, 1955
Creator: Schwartz, Roland J. & Magleby, Dan N.
Partner: UNT Libraries Government Documents Department
open access

An evaluation of costs for constructing high density concrete shields at 105-K

Description: The primary purpose of this report is to present cost data associated with the recent construction of biological shields at Hanford. These data are useful for analyzing shields which have been built during the past four years and for ascertaining ways to improve future designs. Specifically, the objectives of this study are to: compile and analyze cost data associated with the construction of the high density concrete shields at 105-K and the steel-masonite shields at 105-C; and determine unit … more
Date: November 7, 1955
Creator: Davis, H. S.
Partner: UNT Libraries Government Documents Department
open access

The New Element Fermium, Atomic Number 100

Description: No Description Available.
Date: April 7, 1955
Creator: Ghiorso, A.; Thompson, S. G.; Higgins, G. H. & Seaborg, G. T.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip

Description: From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devic… more
Date: April 7, 1955
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department
open access

Flight measurements of directional stability to a Mach number of 1.48 for an airplane tested with three different vertical tail configurations

Description: Report presenting flight tests to measure the directional stability of a fighter-type airplane over a range of Mach numbers. Testing occurred at two altitudes and used three vertical tails of varying aspect ratio or area.
Date: October 7, 1955
Creator: Drake, Hubert M.; Finch, Thomas W. & Peele, James R.
Partner: UNT Libraries Government Documents Department
open access

A variable-geometry axisymmetric supersonic inlet with telescoping centerbody

Description: Report presenting an examination of the use of an axisymmetric variable-geometry technique for achieving good supersonic inlet performance over a wide range of Mach numbers. An inlet with a telescoping spike was designed and experimentally evaluated. Results regarding the spike survey study and variable-geometry-inlet study are provided.
Date: September 7, 1955
Creator: Connors, James F. & Meyer, Rudolph C.
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics of axisymmetric two-cone and isentropic nose inlets at Mach number 1.90

Description: Report presenting an experimental investigation at Mach number 1.90 to determine the overall performance capabilities of axisymmetric two-cone and isentropic nose inlets in terms of total-pressure recovery, mass flow, and external drags. At zero angle of attack, the external drag was separated into their components of cowl pressure, friction, and additive drags. Results regarding total-pressure recovery and mass-flow characteristics, total-pressure profiles at diffuser exit, cowl-pressure distr… more
Date: September 7, 1955
Creator: Connors, James F. & Meyer, Rudolph C.
Partner: UNT Libraries Government Documents Department
open access

Design and test of mixed-flow impellers 6: performance and parabolic-bladed impeller with shroud redesigned by rapid approximate method

Description: Report presenting a centrifugal impeller with a modified design procedure to reduce the velocity gradients existing along the hub from inlet to outlet. The modified impeller had better performance characteristics than the original at all speeds tested.
Date: September 7, 1955
Creator: Smith, Kenneth J. & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department
open access

A theoretical analysis of the effect of engine angular momentum on longitudinal and directional stability in steady rolling maneuvers

Description: From Summary: "The effect of engine momentum on the longitudinal and directional stability of aircraft in steady rolling maneuvers has been investigated. The results presented indicate that the gyroscopic moments produced on the aircraft by rotating engine in rolling maneuvers can have an appreciable effect on the range of rolling velocities for which longitudinal or directional instability might occur."
Date: October 7, 1955
Creator: Gates, Ordway B., Jr. & Woodling, C. H.
Partner: UNT Libraries Government Documents Department
open access

Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles

Description: Report presenting an analysis made to permit a comparative evaluation of the turbine rotor cooling-air requirements with convection-cooled blades for four combustor-outlet radial gas-temperature profiles: a uniform profile, a profile representable by a complete cycle of the cosine wave using cooler gas layers near the turbine casing, a profile representable by one-half cycle of the cosine wave using cooler gas layers near the stator inner ring, and an optimum profile resulting in the absolute m… more
Date: September 7, 1955
Creator: Hubbartt, James E. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
open access

A Low-Pressure-Loss Short Afterburner for Sea-Level Thrust Augmentation

Description: Memorandum presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date: June 7, 1955
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of a Roll-Stabilized Ramjet Test Vehicle Over a Mach Number Range of 2.3 to 2.7

Description: Report presenting a flight investigation on a roll-stabilized ramjet test vehicle to determine engine performance over a range of Mach numbers, a range of fuel-air ratio, and an altitude range. Results regarding engine performance and roll autopilot performance are provided.
Date: October 7, 1955
Creator: Kennedy, Thomas L. & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Flight experience with a delta-wing airplane having violent lateral-longitudinal coupling in aileron rolls

Description: From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceler… more
Date: October 7, 1955
Creator: Sisk, Thomas R. & Andrews, William H.
Partner: UNT Libraries Government Documents Department
open access

A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 2

Description: Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail 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 several angles of attack.
Date: September 7, 1955
Creator: White, Maurice D.
Partner: UNT Libraries Government Documents Department
open access

Preliminary experimental investigation of a variable-area, variable-internal-contraction air inlet at Mach numbers between 1.42 and 2.44

Description: Report presenting a preliminary investigation of a variable-area, variable-internal-contraction air inlet at a range of Mach numbers. The total pressure recovery after supersonic compression, total pressure recovery at the exit of the subsonic diffuser, and the pressure distribution along the diffuser walls were measured.
Date: September 7, 1955
Creator: Scherrer, Richard & Gowen, Forrest E.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of a Roll-Stabilized Ram-Jet Test Vehicle Over a Mach Number Range of 2.3 to 2.7

Description: Report presenting a flight investigation on a roll-stabilized ram-jet test vehicle over a range of Mach numbers from 2.3 to 2.7, a range of fuel-air ratio from 0.038 to 0.050, and an altitude range from 3,000 to 40,000 feet. Results regarding test conditions, engine performance, and roll autopilot performance are provided. The engines operated satisfactorily over the test time and the roll-control system operated satisfactorily at the beginning of testing.
Date: October 7, 1955
Creator: Kennedy, Thomas L. & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Experimental performance of fluorine-oxygen with JP4 fuel in a rocket engine

Description: Report presenting the performance increase resulting from the addition of fluorine to the oxygen-JP4 rocket propellant combination evaluated experimentally in a 1000-pound-thrust engine with 0, 30, and 70 percent of fluorine by weight in the oxidant. Maximum specific impulse values obtained were 259, 278, and 287 pound-seconds per pound, respectively, at a combustion pressure of 600 pounds per square inch absolute.
Date: July 7, 1955
Creator: Douglass, Howard W.
Partner: UNT Libraries Government Documents Department
open access

Acceleration Characteristics of a Turbojet Engine With Variable-Position Inlet Guide Vanes

Description: Report presenting a study of the acceleration characteristics of a turbojet engine equipped with variable-position inlet guide vanes in the altitude test chamber. Maximum acceleration values for 3 engines of the same model were also obtained during testing and were found to differ as much as 50 percent. Results regarding the effect of fuel step size and inlet guide vane on acceleration, effect of flight condition, reproducibility of engine acceleration, compressor pressure ratio in relation to … more
Date: July 7, 1955
Creator: Dobson, W. F. & Wallner, Lewis E.
Partner: UNT Libraries Government Documents Department
open access

A low-pressure-loss short afterburner for sea-level thrust augmentation

Description: Report presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand using the power section of a 5970-pound-thrust, axial-flow turbojet engine. The various portions of the afterburner and procedures used to test it are described. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date: June 7, 1955
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Partner: UNT Libraries Government Documents Department
open access

Free-spinning-tunnel investigation to determine the effect of spin-recovery rockets and thrust simulation on the recovery characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA DE 392

Description: Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.
Date: February 7, 1955
Creator: Burk, Sanger M., Jr. & Lee, Henry A.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Flight-Determined Pressure Distributions Over the Wing of the Douglas X-3 Research Airplane at Subsonic and Transonic Mach Numbers

Description: Report presenting preliminary flight-measured chordwise pressure distributions, which have been obtained at a wing midsemispan station of the Douglas X-3 research airplane through a range of angles of attack and Mach numbers. An exploration of the section aerodynamic characteristics is also provided.
Date: April 7, 1955
Creator: Jordan, Gareth H. & Hutchins, C. Kenneth, Jr.
Partner: UNT Libraries Government Documents Department
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