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The hazards to humans of wildfowl on REDOX contaminated swamp

Description: Ducks, geese, coots, and other wild birds, both migratory and resident, have been swimming on the Redox waste water pond and eating the herbage and mud on the bottom. The pond is caused by the discharge of five to ten million gallons of water a day from the heating and cooling coils of reactor vessels in the Redox plant. At least twice in recent months leaks in the coils have permitted solutions of radioactive material to escape to the swamp. Once the leak was in the waste concentrator tank and… more
Date: December 23, 1952
Creator: Clukey, H. V.
Partner: UNT Libraries Government Documents Department
open access

A Manual of HRE Control and Instrumentation

Description: Technical reports outlining the controls for the Homogeneous Reactor Experiment (HRE); controls are divided into three principal groups. 1. Reactor. 2. Process or auxiliary. 3. Power generation. These are the classifications designating the primary functions of the controls. [From Introduction]
Date: January 23, 1952
Creator: Quarles, L. R. & Walker, W. P.
Partner: UNT Libraries Government Documents Department
open access

Remote mechanical operating methods vs rubber glove operating methods for the 234-5 process

Description: The present RMA Line has now progressed through the run-in period and is engaged in actual production. Considerable new data and experiences are available for use in an evaluation of the basis used for design of the equipment in regard to contamination control and the safety of operating and maintenance personnel. Research and development funds have been allocated to the improvement of the 234-5 process equipment. Thus it is desirable that an up-to-date basis be established for use as criteria … more
Date: September 23, 1952
Creator: Ingalls, W.P.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Several Supersonic Missile Configurations Directed Toward Minimizing Center-of-Pressure Travel

Description: Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.
Date: September 23, 1952
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department
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 of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.
Date: September 23, 1952
Creator: Chubb, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91

Description: Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date: September 23, 1952
Creator: Cahill, Jones F. & Nuber, Robert J.
Partner: UNT Libraries Government Documents Department
open access

Low-speed investigation of the effects of nacelles on the longitudinal aerodynamic characteristics of a 60 degree sweptback delta-wing - fuselage combination with NACA 65A003 airfoil sections

Description: Report presenting an investigation in the full-scale tunnel to determine the effects of symmetrically located wing nacelles on the low-speed aerodynamic characteristics of a 60 degree sweptback delta-wing-fuselage combination. The testing occurred with three spanwise nacelle locations with three chordwise positions at each spanwise station.
Date: July 23, 1952
Creator: Scallion, William I.
Partner: UNT Libraries Government Documents Department
open access

Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21

Description: Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.
Date: June 23, 1952
Creator: Yaker, Charles; Garrett, Floyd B. & Sikora, Paul F.
Partner: UNT Libraries Government Documents Department
open access

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip with freedom in roll. The results indicated that the longitudinal position of the fighters with respect to the bomber had an important effect on the flight behavior of the coupled configuration.
Date: September 23, 1952
Creator: Bennett, Charles V. & Boisseau, Peter C.
Partner: UNT Libraries Government Documents Department
open access

Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails

Description: Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.
Date: May 23, 1952
Creator: Jaquet, Byron M.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Lateral Stability and Control Characteristics of a High-Speed Fighter Airplane

Description: Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.
Date: September 23, 1952
Creator: Crane, H. L.; Beckhardt, A. R. & Matheny, C. E.
Partner: UNT Libraries Government Documents Department
open access

Low speed stability characteristics of a complete model with a wing of W plan form

Description: Report presenting an investigation of the low-speed static stability characteristics of a complete model equipped with a W wing. The lift-curve slope of the wing-fuselage combination was found to be in good agreement with that predicted by available wing-alone theory. Results regarding the longitudinal characteristics, wing-juncture modifications, and lateral and directional stability characteristics are provided.
Date: April 23, 1952
Creator: Polhamus, Edward C. & Becht, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements at Mach Numbers From 1.1 to 1.9 of the Zero-Lift Drag of a Twin-Engine Supersonic Ram-Jet Configuration

Description: Report presenting a flight investigation to determine the zero-lift drag characteristics of a twin-engine supersonic ramjet configuration in order to make performance calculations below the design Mach number. Data was obtained over a range of Mach numbers for two power-off ramjet models with and without nacelles. Information about the variation of Reynolds number, total and external drag coefficients, and model-component drag coefficients is provided.
Date: June 23, 1952
Creator: Leiss, Abraham
Partner: UNT Libraries Government Documents Department
open access

The effects of tip-mounted jet nacelles on the transonic characteristics of low-aspect-ratio wings

Description: Report presenting an investigation of the effects of tip-mounted jet-engine nacelles on the aerodynamic characteristics of low-aspect-ratio rectangular and tapered wings using the transonic-bump technique. The effect of the tip-mounted nacelles was generally to increase the lift-curve slopes for wings of aspect ratio 2 or larger with upper or lower mounted nacelles causing larger increases than symmetrically mounted nacelles. Results regarding rectangular wings and tapered wings are provided.
Date: December 23, 1952
Creator: Coe, Charles F.
Partner: UNT Libraries Government Documents Department
open access

A Method for Estimating Speed Response of Gas-Turbine Engines

Description: Memorandum presenting a brief method for estimating the speed response of turbojet and turbine-propeller engines to a step change in fuel flow. The method approximates the dynamic equilibrium in the gas-turbine engine with a first-order linear differential equation, the time constant of which varies inversely with the equilibrium speed. Engine time constants computed by means of this method are compared with time-constant data obtained by direct measurement of transient on three turbojet engine… more
Date: January 23, 1952
Creator: Gold, Harold & Rosenzweig, Solomon
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9

Description: Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
Date: December 23, 1952
Creator: Ulmann, Edward F. & Dunning, Robert W.
Partner: UNT Libraries Government Documents Department
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