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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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Reactor Irradiation of Thorium-Uranium Alloy Fuel Plates

Description: Several plates of 98.7% Th - 1.2% U 235 (clad in aluminum) were irradiated in the MTR for an integrated flux of 2.6 x 10 21 neutrons/cm2. Although these samples represent an early development in bonding of aluminum to thorium and there are better methods at present, the bond proved to be quite strong and both clad and core were dimensionally stable under irradiation. The production of uranium 233 was as much as theory would indicate and the total amount of fissionable material material after ir… more
Date: September 7, 1955
Creator: Carrell, R. M.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Practical Methods for the Reduction of Strain Gage Data

Description: The error that results when it is attempted to evaluate stress from a reading taken on a single element SR-4 strain gage in a biaxial stress field is discussed. A method is presented for relating SR-4 rosette strain gage readings directly to the biaxial stress state without the necessity of first converting strain gage readings to true strains. Correction formulas are presented for use when single element SR-4 gages are used as rosette elements or as stress gages.
Date: September 7, 1955
Creator: Dove, Richard C.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B

Description: Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Date: July 7, 1955
Creator: Hamrick, Joseph T. & Osborn, Walter M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Physics Research Quarterly Report: July, August, September 1955

Description: Under the general heading of Reactor Lattices are reported a new method of calculating resonance escape probabilities, results for the effective mass of a proton bound in the water molecule, and a comparison of similar techniques for calculating lattice constants developed independently by Hanford physicists and by a school of Russian physicists (as reported at the Geneva Conference). An estimate of maximum errors in f and η for thermal systems is described. Experiments and analysis thereof on … more
Date: December 7, 1955
Creator: Hanford Atomic Products Operation. Engineering Department. File Technology Section. Physics Research Sub-Section.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Injection Principles from Combustion Studies in a 200-Pound-Thrust Rocket Engine Using Liquid Oxygen and Heptane

Description: "The importance of atomizing and mixing liquid oxygen and heptane was studied in a 200-pound-thrust rocket engine. Ten injector elements were used with both steel and transparent chambers. Characteristic velocity was measured over a range of mixture ratios. Combustion gas-flow and luminosity patterns within the chamber were obtained by photographic methods" (p. 1).
Date: June 7, 1955
Creator: Heidmann, M. F. & Auble, C. M.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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