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Kinetic study of mass transfer by sodium hydroxide in nickel under free-convection conditions

Description: An investigation was conducted using static capsules fabricated from "L" nickel tubing to determine the effect of temperature level, temperature gradient, and test duration on corrosion and mass transfer by molten sodium hydroxide under free-convection conditions. A base temperature range from 1000 degrees to 1600 degrees F with temperature differences to 500 degrees was studied. The rate of mass transfer was found to be strongly dependent on both temperature level and gradient. The rate shows … more
Date: March 10, 1954
Creator: Mosher, Don R. & Lad, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Flow in an Annular-Diffuser-Tailpipe Combination With an Abrupt Area Expansion and Suction, Injection, and Vortex-Generator Flow Controls

Description: Report presenting an investigation of the performance of an annular-diffuser-tailpipe combination with an abrupt area expansion with and without flow controls in the form of suction, injection, and vortex generators. Results regarding the inlet measurements, longitudinal static-pressure distribution, radial distributions, and mean performance coefficients are provided.
Date: February 10, 1954
Creator: Henry, John R. & Wilbur, Stafford W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine

Description: "A preliminary evaluation was made of three types of combustor configurations in a 48-inch-diameter ram-jet engine to determine the one with the greatest promise of ultimately achieving efficient and stable combustion at low fuel-air rations and low combustor-inlet pressure. The combustor configurations evaluated include (1) a can-piloted configuration using a gutter-type flame holder with can-type pilot burners for stability, (2) an annular-piloted configuration using a gutter-type flame holde… more
Date: March 10, 1954
Creator: Meyer, Carl L. & Welna, Henry J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Effects of Flame-Holder Gutter Shape on Afterburner Performance

Description: Report presenting an investigation of the effect of flame-holder gutter cross-sectional shape on afterburner performance in an afterburner test rig. Fuel-air distribution and burner inlet temperature were held as constant as possible for all of the shapes. Results regarding the burner flow conditions, typical performance characteristics, and effect of flame-holder gutter shape on combustion efficiency, pressure loss, and stability limits are provided.
Date: February 10, 1954
Creator: Nakanishi, S.; Velie, W. W. & Bryant, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61

Description: Report presenting an investigation at Mach number 1.61. to determine the aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a partial-span spoiler mounted on the wing just ahead of the control. Pressure distribution and hinge-moment measurements were made over a range of angles of attack and control deflection. Results indicated that regions of increase pressure due to flow separation ahead of the control at the larger control deflections… more
Date: March 10, 1954
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Additional Fatigue Tests on Effects of Design Details in 355-T6 Sand-Cast Aluminum Alloy

Description: From Introduction: "Reported herein are results of the additional direct-stress fatigue tests on: (1) a plate-type specimen with cored centrally located hole and (2) 0.300-inch-diameter round polished specimens with various degrees of porosity."
Date: March 10, 1954
Creator: Eaton, I. D. & Youra, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Altitude-Ignition Characteristics of Three Fuels of Different Volatility in a Turbojet Engine

Description: Report presenting an investigation on a full-scale turbojet engine to obtain the altitude-ignition characteristics of three fuels with different ASTM distillation curves. Two of the fuels had a Reid vapor pressure of 2.7 pounds per square inch and the third had a vapor pressure of 1.7 pounds per square inch. Results regarding the effect of fuel volatility and fuel-air ratio on altitude-ignition and propagation characteristics and effect of altitude variation on altitude ignition and propagation… more
Date: March 10, 1954
Creator: Braithwaite, Willis M. & Sivo, Joseph N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Measurements of Turbulence and Temperature Fluctuations Behind a Heated Grid

Description: "Preliminary measurements have been made of velocity and temperature fluctuations in the flow behind a heated grid in a uniform airstream. Temperature correlation shows a reasonable degree of isotropy, and the temperature fluctuations die out at large distances more slowly than the turbulence, as has been predicted theoretically under some strongly simplifying postulates" (p. 1).
Date: June 10, 1954
Creator: Kistler, A. L.; O'Brien, V. & Corrsin, S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Drag and Opening Characteristics of a Kaman Rotochute Model

Description: Report presenting an experimental investigation in the 7- by 10-foot tunnel in a range of Mach numbers to determine the drag and opening characteristics of a model of a Kaman Aircraft Corporation Rotochute. The Rotochute is a two-bladed flapping rotor with governor-controlled blades designed for lowering cargo containers from high-speed aircraft tested at various Mach numbers simulating constant rates of descent.
Date: June 10, 1954
Creator: Lockwood, Vernard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight determination of the drag of conical-shock nose inlets with various cowling shapes and axial positions of the center body at Mach numbers from 0.8 to 2.0

Description: Report presenting free-flight testing of conical-shock nose inlet models with cowls of fineness ratio 3 with five different profiles. Three of the profiles were mostly conic with different lip shapes, one was parabolic, and one was NACA 1-series. Results regarding the basic data, effect of cone position, comparison of profile shapes, and effect of mass-flow ratio are provided.
Date: September 10, 1954
Creator: Merlet, Charles F. & Putland, Leonard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet effects on pressure loading of all-movable horizontal stabilizer

Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the effects of a cold exhaust jet on the pressure loadings of an all-movable, 45 degree sweptback horizontal stabilizer located in a region influenced by the jet. Results indicated that at jet pressure ratios of 1 to 9, the exhaust jet did not appreciably affect the pressure loadings of the stabilizer.
Date: June 10, 1954
Creator: Valerino, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of slurries of 50 percent boron in JP-4 fuel in 5-inch ram-jet burner

Description: Report presenting the performance of slurries of 50 percent boron in MIL-F-5624A grade JP-4 fuel evaluated in a 5-inch ramjet burner. Boron slurries were found to give higher heat outputs than JP-4 fuel only at fuel-air ratios above stoichiometric for JP-4 fuel. Testing found that it was also possible to determine the flow properties of particular batches of slurry before burning by flowing them through a bench system which would simulate the actual fuel system that would use the slurry.
Date: June 10, 1954
Creator: Reynolds, Thaine W. & Haas, Donald P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Stability and Control Characteristics at a Mach Number of 1.61 of the Complete Configuration Equipped With Spoilers

Description: Report discussing an investigation to determine the stability and control characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing and equipped with spoiler lateral control devices at Mach number 1.61. The effects of various types of spoilers, spoiler span, spoiler projection, and chordwise location were investigated, as well as the hinge-moment characteristics of the plain spoiler.
Date: September 10, 1954
Creator: Hamilton, Clyde V. & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer

Description: Report presenting an experimental investigation to evaluate the internal performance of two types of auxiliary air inlets, a submerged and a scoop inlet, operating within the turbulent boundary layer existing on the bottom of a typical supersonic fighter aircraft afterbody. Results regarding boundary-layer flow and inlet performance are provided.
Date: March 10, 1954
Creator: Pennington, Donald B. & Simon, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An air-flow-direction pickup suitable for telemetering use on pilotless aircraft

Description: From Summary: Test results are presented which indicate that the pickup is aerodynamically stable and has accuracy, obtained from a bench calibration, of better than 0.3^o under conditions including acceleration up to 20g in any direction, Mach numbers from 0.5 to 2.8, and dynamic pressures up to at least 65 psi. Equations and curves which can be used to obtain flow direction at the center of gravity of a maneuvering model are presented."
Date: March 10, 1954
Creator: Ikard, Wallace L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Rocket-Motor Operation on the Drag of Three 1/5-Scale Hermes A-3A Models in Free Flight

Description: Three 1/5-scale models of the Hermes A-3A missile have been flown to determine the effect of rocket-motor operation on the drag corresponding to various altitude and Mach number combinations. The flights covered a Mach number range from 0.5 to 1.8, and ratios of jet-exit static pressure to free-stream static pressure from 0.8 to 1.8. The results indicate that the power-on drag of the missile should be the same as the power-off drag at Mach number 1.3 and slightly less than the power-off drag at… more
Date: February 10, 1954
Creator: Jackson, H. Herbert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Wing Leading-Edge Camber and Tip Modifications on the Aerodynamic Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds

Description: "The effects of several wing leading-edge camber and deflected-tip modifications on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane have been determined at Mach numbers from 0.60 to 1.14 for angles of attack up to 14 degrees in the Langley 8-foot transonic tunnel. The effects of elevator deflections from 0 deg. to -10 deg. were also obtained for a configuration incorporating favorable leading- edge and tip modifications. Leading-edge modifications which … more
Date: November 10, 1954
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Description: "Additional results on the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane were obtained in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.92. The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. The sideslip-angle range investigated was from -4 degrees to 12 degrees" (p. 1).
Date: August 10, 1954
Creator: Spreeman, Kenneth P. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Three Low-Temperature-Ratio Combustor Configurations in a 48-Inch-Diameter Ram-Jet Engine

Description: Memorandum presenting a preliminary evaluation of three types of combustor configuration in a 48-inch-diameter ramjet engine in order to select the one with the greatest promise of efficient and stable combustion at low fuel-air ratios and low combustor-inlet pressures. Results regarding the inlet conditions, performance, and a comparison of the configurations are provided.
Date: March 10, 1954
Creator: Meyer, Carl L. & Weina, Harry J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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