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Some fundamental aspects of nitric acid oxidants for rocket applications

Description: From Summary: "The literature pertaining to the preparation, physical properties, corrosiveness, thermal stability, constitution, and analysis of various nitric acids is reviewed primarily with respect to their use as rocket oxidants. Conflicting data are evaluated and recommendations for additional experimental work are indicated. Reactions of nitric acid which could occur during the starting and steady-stage phases of rocket operation are discussed and probable mechanisms are selected on the … more
Date: January 14, 1953
Creator: Ladanyi, Dezso J.; Miller, Riley O.; Karo, Wolf & Feiler, Charles E.
Partner: UNT Libraries Government Documents Department
open access

Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture

Description: Report presenting an investigation to determine the effect of turbulence generated by different sizes of wire grid on the minimum spark-ignition energy of a flowing propane-air mixture. Gas-stream velocity, size of turbulence promoter, and distance from the promoter plate to the electrodes on minimum ignition energy were evaluated and the effects are shown in figures.
Date: January 14, 1953
Creator: Swett, Clyde C., Jr. & Donlon, Richard H.
Partner: UNT Libraries Government Documents Department
open access

Performance of a turbojet engine with adjustable first-stage turbine stator and variable-area exhaust nozzle

Description: The performance of a turbojet engine with a two-stage turbine, an adjustable first-stage turbine stator, and a variable-area exhaust nozzle was investigated at selected constant engine speeds and two simulated flight conditions. For the particular component characteristics of the engine investigated, little improvement in thrust levels of interest by use of an adjustable rather than an optimum fixed first-stage turbine stator.
Date: August 14, 1953
Creator: Meyer, Carl L.; Smith, Ivan D. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
open access

Free-flight tests of three 1/9-scale models of the wing-ram-jet configuration of the Grumman XSSM-N-6A (Rigel) missile to investigate the possibility of flutter: TED No. NACA DE 223

Description: Report presenting cold-flow free-flight tests at zero lift to investigate the possibility of flutter of simulated wing-ram-jet-nacelle configurations which were 1/9-scale models of the wing and ramjet nacelles of the Grumman XSSM-N-6a missile. Testing was performed on three different configurations. Results regarding Mach number, velocity, aerodynamic density, and flutter are provided.
Date: April 14, 1953
Creator: O'Kelly, Burke R. & Lauten, William T., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Spoiler Ailerons with and Without a Gap Behind the Spoiler on a 45 Degree Sweptback Wing-Fuselage Combination at Mach Numbers from 0.60 to 1.03

Description: Report presenting an investigation conducted with several 73-percent semispan inboard spoiler ailerons, projecting 4 percent of the local wing chord from the wing surface, and located at the 70-percent chord line of a 45 degree sweptback wing-fuselage combination. Results regarding the effect of upper-surface spoilers on basic model characteristics, effect of gap on spoiler characteristics, comparison of upper- and lower-surface spoiler characteristics, comparison of upper-surface spoiler with … more
Date: September 14, 1953
Creator: West, F. E., Jr.; Solomon, William & Brummal, Edward M.
Partner: UNT Libraries Government Documents Department
open access

The lateral control characteristics of constant-percent-chord trailing-edge elevons on a pointed wing of aspect ratio 2 at Mach numbers up to 0.95

Description: Report presenting an investigation to determine the lateral control characteristics of constant-percent-chord trailing-edge elevons on a tailless wing-body combination with a pointed wing of aspect ratio 2. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results include the lift, drag, pitching moment, rolling moment, elevon hinge moment, tab moment, elevon load, and center of pressure of elevon load.
Date: August 14, 1953
Creator: Reed, Verlin D. & Smith, Donald W.
Partner: UNT Libraries Government Documents Department
open access

The Influence of a Change in Body Shape on the Effects of Twist and Camber as Determined by a Transonic Wind-Tunnel Investigation of a 45 Degree Sweptback Wing-Fuselage Configuration

Description: Report presenting an investigation in the transonic tunnel to determine the influence of a change in body shape on the effects of twist and camber. Twist and camber were found to greatly improve the maximum lift-drag ratios of the wing-modified fuselage configuration through the speed range, but reduced the ratios for a wing-curved fuselage configuration. Results regarding basic aerodynamic data are also provided.
Date: August 14, 1953
Creator: Harrison, Daniel E.
Partner: UNT Libraries Government Documents Department
open access

Effect of Large Deflection of a Canard Control and Deflections of a Wing-Tip Control on the Static-Stability and Induced-Roll Characteristics of a Cruciform Canard Missile at a Mach Number of 2.01

Description: Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the static stability and control characteristics of a canard-type missile configuration with large deflections of the canard controls and with deflection of wing-tip controls. The results of the investigation indicated that with a 30 degree deflection of the canard control a maximum trim normal-force coefficient of 0.4 and a maximum trim angle of attack of 12 degrees … more
Date: December 14, 1953
Creator: Spearman, M. Leroy
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Use of a Stick Force Proportional to Pitching Acceleration for Normal-Acceleration Warning

Description: Report presenting an investigation of the feasibility of modifying the transient portion of the stick force in abrupt maneuvers in order to eliminate inadvertent normal-acceleration overshoots. The modification consists of additional stick force proportional to a quantity which leads the normal acceleration. The characteristics introduced by the inclusion of the force were considered to be very desirable by pilots.
Date: August 14, 1953
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation to determine effects of rectangular vortex generators on the static pressure drop through a 90 degrees circular elbow

Description: Report presenting an investigation of a constant-area, circular 90 degree elbow of mean radius of curvature equal to its diameter with several arrangements of simple, nontwisted, rectangular vortex generators. The inlet flow had a boundary layer of about one-tenth the duct diameter. Results regarding an elbow with no vortex generators and an elbow with vortex generators are provided.
Date: September 14, 1953
Creator: Valentine, E. Floyd & Copp, Martin R.
Partner: UNT Libraries Government Documents Department
open access

Analytical evaluation of effect of equivalence ratio inlet-air temperature and combustion pressure on performance of several possible ram-jet fuels

Description: The results of an analytical investigation of the theoretical air specific impulse performance and adiabatic combustion temperatures of several possible ram-jet fuels over a range of equivalence ratios, inlet-air temperatures, and combustion pressures, is presented herein. The fuels include octane-1, 50-percent-magnesium slurry, boron, pentaborane, diborane, hydrogen, carbon, and aluminum. Thermal effects from high combustion temperatures were found to effect considerably the combustion perform… more
Date: September 14, 1953
Creator: Tower, Leonard K. & Gammon, Benson E.
Partner: UNT Libraries Government Documents Department
open access

Exploratory Investigation of Transpiration Cooling to Alleviate Aerodynamic Heating on an 8 Degree Cone in a Free Jet at a Mach Number of 2.05

Description: Report presenting testing of the effectiveness of transpiration cooling of an 8 degree total angle conical body with water removed onto the surface through a porous section near the nose. Results regarding a reference test without cooling, a cooling test with 0.010 pound of water per second, a cooling test with 0.0025 pound of water per second, a hypothesis of the phenomena of liquid transpiration cooling, water consumption are provided.
Date: September 14, 1953
Creator: O'Sullivan, William J.; Chauvin, Leo T. & Rumsey, Charles B.
Partner: UNT Libraries Government Documents Department
open access

Performance comparison of three canard-type ram-jet missile configurations at Mach numbers from 1.5 to 2.0

Description: Report presenting performance characteristics of three similar canard-type, long-range ram-jet missiles to evaluate the relative merits of several types of engine installation. Some of the engine installations included a twin-engine nacelle-type installation strut-mounted above and below the fuselage, a twin-engine nacelle-type installation mounted on the wing, and a single-engine fuselage-contained installation with an underslung scoop-type inlet.
Date: August 14, 1953
Creator: Fradenburgh, Evan A. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department
open access

Altitude operational characteristics of prototype J40-WE-8 turbojet engine

Description: From Introduction: "The altitude performance characteristics of the prototype J40-WE-8 turbojet engine were determined in the NACA Lewis altitude wind tunnel. The altitude operational characteristics of the engine are presented herein. The results of a brief study of the effect of the two different grades of fuel (MIL-F-5624A grades JP-3 and JP-4) on steady-state engine performance at an altitude of 45,000 feet and a flight Mach number of 0.20 are also given."
Date: August 14, 1953
Creator: Sobolewski, Adam E. & Lubick, Robert J.
Partner: UNT Libraries Government Documents Department
open access

Effect of leading-edge chord-extensions on the aerodynamic characteristics of a 45 degree sweptback wing-fuselage combination at Mach numbers of 0.40 to 1.03

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effect of leading-edge chord-extensions on the aerodynamic characteristics of a sweptback wing-fuselage combination at several Mach numbers. Results regarding the effect of chord-extensions on longitudinal stability for wing-normal configuration, effect of chord extensions on lift for wing-normal configurations, effect of chord-extensions on drag and lift-drag ratios of wing-normal configurations, effect of chor… more
Date: April 14, 1953
Creator: West, F. E., Jr.; Martz, Gladys S. & Liner, George
Partner: UNT Libraries Government Documents Department
open access

The Slow Neutron Capture Cross Section of Carbon¹³

Description: From abstract: "The cross section of carbon for the n, y reaction was determined using samples of graphite, barium carbonate and carbon dioxide. The results were consistent only when samples were used which were enriched in C¹³."
Date: August 14, 1953
Creator: Hennig, Gerhart R.
Partner: UNT Libraries Government Documents Department
open access

Note of the Function of the Aquadag in the Stellarator

Description: The following report introduces the aquadag, a part of the stellarator with the purposes to prevent the non-uniform accumulation of electrostatic charges on the walls of the stellerator and to free the electrons of the stellerator and provide accelerations, achieving a uniform field distribution.
Date: January 14, 1953
Creator: Witten, Louis
Partner: UNT Libraries Government Documents Department
open access

Corrosion of Aluminum and Beryllium by MTR Canal Water

Description: Introduction: "In the early operation of the WTR severe canal corrosion of dummy fuel assemblies and a beryllium A-piece caused a great deal of concern as to the possible effects of long-time canal storage on such elements. A short-term experimental program was started to determine the causes of this corrosion and to correct them before any irradiated fuel elements had to be stored in the canal. The results of this program are presented here."
Date: January 14, 1953
Creator: Burnham, J. B., Jr. & Bartz, M. H.
Partner: UNT Libraries Government Documents Department
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