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Fused Fluoride--Inconel System Under Cyclotron Irradiation--Preliminary Results

Description: The fused fluoride-Inconel reactor system was studied under irradiation with nominal 19 Mev deuterons as supplied by the Berkeley 60-inch cyclotron. Chemical, metallographic, magnetic susceptibility, electron diffraction and X-ray diffraction studies were made on the as-received materials, one control run and two irradiated runs. No changes in the fused fluoride fuel were noted. Accelerated intergranular corrosion and increased grain size were observed in the irradiated Inconel specimens. This … more
Date: December 17, 1951
Creator: Goeddel, W.V. & Epp, Jr., A.A.
Partner: UNT Libraries Government Documents Department
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A Fast Neutron Detector

Description: No Description Available.
Date: October 17, 1951
Creator: Hornyak, W. F.
Partner: UNT Libraries Government Documents Department
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A correlation by means of transonic similarity rules of experimentally determined characteristics of a series of symmetrical and cambered wings of rectangular plan form

Description: Transonic similarity rules are applied to the correlation of experimental data for a series of related rectangular wings of varying aspect ratio, thickness, and camber. The data correlation is presented in two parts: the first part presents the correlation for a series of 22 wings having symmetrical NACA 63a-series sections; the second part is concerned with a study of one type of camber by correlation of the data for a series of 18 cambered wings having NACA 63a2xx and 63a4xx sections.
Date: December 17, 1951
Creator: McDevitt, John B.
Partner: UNT Libraries Government Documents Department
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Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control

Description: From Introduction: "This report shows correlation between actual transient data obtained from the engine and solutions to a simulated system set up on an analog computer. Data are presented for response of engine speed to changes in set speed when the power plant was being controlled by a relay-type electronic governor that acted to maintain set speed by varying propeller pitch. Correlation obtained for sea-level conditions between actual time data and analog solutions is discussed."
Date: May 17, 1951
Creator: Vasu, George & Pack, George J.
Partner: UNT Libraries Government Documents Department
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Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Chordwise Positions at the Wing Tip of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the chordwise position of a nacelle at the wing tip of a 45 degree sweptback wing and body combination as determined through transonic flight tests at zero lift. The drag of the configuration with nacelles in the rear chordwise positions was equal to or less than the drag of the configuration without nacelles over most of the speed range.
Date: September 17, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department
open access

A semi-empirical method for calculating the pitching moment of bodies of revolution at low Mach numbers

Description: A semiempirical method, in which potential theory is arbitrarily combined with an approximate viscous theory, for calculating the aerodynamic pitching moments for bodies of revolution is presented. The method can also be used for calculating the lift and drag forces. The calculated and experimental force and moment characteristics of 15 bodies of revolution are compared.
Date: May 17, 1951
Creator: Hopkins, Edward J.
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Longitudinal Stability and Control Characteristics at Mach Numbers Up to 0.87

Description: Report presenting flight measurements using the Douglas D-558-II airplane in order to determine the longitudinal stability and control characteristics in steady and accelerated flight. Results are given for various flap positions, especially in regards to degrees of instability present.
Date: January 17, 1951
Creator: Sjoberg, S. A.; Peele, James R. & Griffith, John H.
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Ram-Jet-Engine Performance in Flight Mach Number Range From 3 to 7

Description: "An analytical investigation was made of the performance of isolated ram-jet engines in the flight Mach number range from 3 to 7 for two types of diffuser, a high-efficiency diffuser, and a normal-shock diffuser. The fuel was assumed to be a hydrocarbon similar to gasoline. The conclusions reached are: (1) a design altitude of about 100,000 feet is desirable for a high-efficiency high Mach number ram jet on the basis of engine construction and performance; and (2) although greater thrust could … more
Date: October 17, 1951
Creator: Evans, Philip J., Jr.
Partner: UNT Libraries Government Documents Department
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Estimation of Neutron Energy for First Resonance From Absorption Cross Section for Thermal Neutrons

Description: Examination of published data for some 52 isotopes indicates that the neutron energy for which the first resonance occurs is related to the magnitude of the thermal absorption cross section. The empirical relation obtained is in qualitative agreement with the results of a simplified version of the resonance theory of the nucleus of Breit-Wigner.
Date: September 17, 1951
Creator: Bogart, Donald
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of a fin-actuated jet-vane control system for stabilization of rocket-powered models

Description: Report presenting aerodynamic parameters and operation techniques for a fin-actuated jet-vane system for the stabilization of a rocket-powered model by means of static and flight tests. Static testing was used to obtain lift, hinge moment, and center-of-pressure location of the jet vane, while the longitudinal stability characteristics of a simplified model were determined from the results of a flight test.
Date: January 17, 1951
Creator: Wineman, Andrew R.
Partner: UNT Libraries Government Documents Department
open access

Full-scale investigation of cooling shroud and ejector nozzle for a turbojet engine: afterburner installation

Description: From Summary: "A full-scale ejector cooling investigation was made on a turbojet engine - afterburner installation in the NACA Lewis altitude wind tunnel. Ejector performance was studied at primary exhaust-gas temperatures from 2700 degrees to 3400 degrees R (corresponding to ejector temperature ratios from 2.0 to 5.0), primary pressure ratios from 1.79 to 3.4, secondary air flows up to 29 percent of the primary gas flow, and for diameter ratios from 1.08 to 1.42 and spacing ratios from 0.04 to… more
Date: December 17, 1951
Creator: Wallner, Lewis E. & Jansen, Emmert T.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Aerodynamic Characteristics of a Series of Cone-Cylinder Configurations at a Mach Number of 6.86

Description: Report presenting the results of pressure-distribution and force tests of two cone-cylinder configurations and a comparison with theoretical calculations. The first series was made up of three configurations with 20 degree conical noses and cylindrical afterbodies with 0, 2, and 4 diameter lengths and the second was made up of cylindrical afterbodies with a diameter length and conical noses with apex angles of 10 to 180 degrees. Results regarding the pressure distributions, aerodynamic forces, … more
Date: December 17, 1951
Creator: Cooper, Ralph D. & Robinson, Raymond A.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of turbojet-engine thrust augmentation by combined compressor coolant injection and tail-pipe burning

Description: Report presenting an investigation of combined compressor coolant injection and tailpipe burning as a means of turbojet engine thrust augmentation at sea-level, zero ram conditions on a 4000 pound thrust, axial-flow-type turbojet engine. Water-alcohol injection flows from 2 to 5 pounds per second were introduced into the compressor in conjunction with tail-pipe burner fuel-air ratios from 0.017 to stoichiometric. Results regarding engine performance and operational characteristics are provided.
Date: October 17, 1951
Creator: Useller, James W. & Povolny, John H.
Partner: UNT Libraries Government Documents Department
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Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics: transonic bump method

Description: Report presenting the results of an experimental investigation of the downwash and longitudinal stability characteristics of a semispan, triangular-wing airplane model with a horizontal tail. Lift, drag, and pitching-moment data re presented for the wing-fuselage combination. Results indicated that the model with the tail on or below the wing-chord plane possessed satisfactory stability characteristics throughout the test range of lift coefficient.
Date: August 17, 1951
Creator: Allen, Edwin C.
Partner: UNT Libraries Government Documents Department
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Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds

Description: Report presenting an investigation of a solid half body modified to mount a scoop inlet and a submerged inlet while maintaining the same entrance geometry, afterbody, and diffuser for both inlets. Comparative pressure-recovery, pressure-distribution, and drag data were obtained for the two inlet types.
Date: December 17, 1951
Creator: Frank, Joseph L. & Taylor, Robert A.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Investigation to Determine the Effect of Two Nose Designs on Spin and Recovery Characteristics of a 1/20-Scale Model of the McDonnel XF3H-1 Airplane: TED No. NACA DE 343

Description: Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/20-scale model to determine the effect of two alternate nose designs on the spin and recovery characterstics of the McDonnel XF3H-1 airplane. The results indicated that, in order to insure satisfactory recovery from any developed spin obtained in the airplane with either of the two alternate nose designs, it may be necessary to use ailerons deflected with the spin in conjunction with rudder reversal, as was the ca… more
Date: August 17, 1951
Creator: Wilson, Jack H.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Cooling-Air Ejector Performance at Pressure Ratios from 1 to 10

Description: Preliminary investigation was made of conical cooling air ejector at primary pressure ratios from 1 to 10. The cooling-air flow was maintained at zero and the resulting pressure variation in the shroud indicated pumping ability. The cooling-air flow was maintained at zero and the resulting pressure variation in the shroud indicated pumping ability.
Date: October 17, 1951
Creator: Ellis, C. W.; Hollister, D. P. & Sargent, A. F., Jr.
Partner: UNT Libraries Government Documents Department
open access

A correlation of experimental zero-lift drag of rectangular wings with symmetrical NACA 65-series airfoil sections by means of the transonic similarity law for wings of finite aspect ratio

Description: Report presenting an application of the transonic similarity law to the correlation of the zero-lift drag of rectangular wings obtained by means of free-fall and rocket techniques. Results regarding the basic data, the modified similarity rule, correlation of data, and similarity law for swept wings are provided.
Date: September 17, 1951
Creator: Danforth, Edward C. B.
Partner: UNT Libraries Government Documents Department
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Investigation of Internal Film Cooling of 1000-Pound-Thrust Liquid-Ammonia - Liquid-Oxygen Rocket-Engine Combustion Chamber

Description: Memorandum presenting an investigation of internal film cooling of the combustion chamber of a 1000-pound-thrust liquid-ammonia-liquid-oxygen rocket engine. The three coolants studied were water, ethyl alcohol, and liquid ammonia. Results regarding heat-transfer results, liquid film-cooled length, correlation of heat-transfer data, and effect of film cooling on performance are provided.
Date: July 17, 1951
Creator: Morrell, Gerald
Partner: UNT Libraries Government Documents Department
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Subsonic Mach and Reynolds number effects on the surface pressures, gap flow, pressure recovery, and drag of a nonrotating NACA 1-series E-type cowling at an angle of attack of 0 degrees

Description: Report presenting a wind-tunnel investigation to evaluate the effects of Mach and Reynolds number on the characteristics of the internal and external flow about an E-type cowling suitable for a turbine-propeller power-plant installation. Results regarding the pressure-coefficient distributions, critical Mach number, cowl-gap flow, ham recovery, and wake-survey drag are provided.
Date: July 17, 1951
Creator: Reynolds, Robert M. & Sammonds, Robert I.
Partner: UNT Libraries Government Documents Department
open access

An investigation of four wings of square plan form at a Mach number of 6.9 in the Langley 11-inch hypersonic tunnel

Description: The results of pressure-distribution and force tests of four wings at a Mach number of about 6.9 and a Reynolds number of 0.98 x 10(6) in the Langley 11-inch hypersonic tunnel are presented. The wings had a square plan form, a 5-percent-chord maximum thickness, and diamond, half-diamond, wedge, and half-circular sections.
Date: April 17, 1951
Creator: McLellan, Charles H.; Bertram, Mitchel H. & Moore, John A.
Partner: UNT Libraries Government Documents Department
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