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Production Test 105-533-A -- Supplement C, Local controlled increases in C-Pile tube powers

Description: Production Test 105--533-A and Supplements A and B which authorize an ``experimental area`` in C-pile in which the tube power limits are relaxed to allow tube power increases up to 16-2/3 per cent above the maximum allowed tube power outside of the experimental area. Supplement B (HW-28775) further limits the maximum tube power to 820 kw. The planned increase of tube powers at C-Pile (from 700 kw/tube to 800 kw/tube) for the tubes outside of the experimental area will cause the experimental are… more
Date: December 29, 1953
Creator: Brugge, B. O.
Partner: UNT Libraries Government Documents Department
open access

Plastic Deformation of Aluminum Single Crystals at Elevated Temperatures

Description: "This report describes the results of a comprehensive study of plastic deformation of aluminum single crystals over a wide range of temperatures. The results of constant-stress creep tests have been reported for the temperature range from 400 degrees to 900 degrees F. For these tests, a new capacitance-type extensometer was designed. This unit has a range of 0.30 inch over which the sensitivity is very nearly linear and can be varied from as low a sensitivity as is desired to a maximum of 20 mi… more
Date: December 29, 1953
Creator: Johnson, R. D.; Young, A. P. & Schwope, A. D.
Partner: UNT Libraries Government Documents Department
open access

Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design

Description: Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
Date: October 29, 1953
Creator: Lockwood, Vernard E.; Luoma, Arvo A. & Solomon, Martin
Partner: UNT Libraries Government Documents Department
open access

Theoretical Performance of Mixtures of Liquid Ammonia and Hydrazine as Fuel With Liquid Fluorine as Oxidant for Rocket Engines

Description: Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are specific impulse, combustion chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal … more
Date: July 29, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department
open access

Component and over-all performance evaluation of a J47-GE-25 turbojet engine over a range of engine-inlet Reynolds number indices

Description: Report presenting an investigation in the altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds number indices. Secondary effects of exhaust-nozzle flow coefficient, air-flow leakage, and inlet temperature should be considered before analyzing the effect of variations in engine-inlet Reynolds number index. Several minor design modifications proposed by the manufacturer did not produce any measurable improvement in engine perform… more
Date: September 29, 1953
Creator: Walker, Curtis L.; Braithwaite, Willis M. & Fenn, David B.
Partner: UNT Libraries Government Documents Department
open access

Procedure for Measuring Liquid-Water Content and Droplet Sizes in Supercooled Clouds by Rotating Multicylinder Method

Description: "The rotating multicylinder method for in-flight determination of liquid-water content, droplet size, and droplet-size distribution in icing clouds is described. The theory of operation, the apparatus required, the technique of obtaining data in flight, and detailed methods of calculating the results, including necessary charts and tables, are presented" (p. 1).
Date: June 29, 1953
Creator: Lewis, William; Perkins, Porter J. & Brun, Rinaldo J.
Partner: UNT Libraries Government Documents Department
open access

Altitude performance characteristics of the J47-25 turbojet engine: data presentation

Description: From Introduction: "An investigation was conducted in an NACA Lewis altitude chamber to determine the altitude performance characteristics of a J47-25 axial-flow turbojet engine over a range of engine-inlet Reynolds number indices corresponding to altitudes from 18,000 to 54,000 feet and flight Mach numbers from 0.50 to 1.10. Reynolds number at a given corrected engine speed and is a function only of engine-inlet total pressure and temperature, was used instead of various set altitudes and flig… more
Date: September 29, 1953
Creator: Renas, Paul E. & Jansen, Emmert T.
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance Investigation of Two Single-Annular Type Combustors and the Prototype J40-WE-8 Turbojet Engine Combustor With Various Combustor-Inlet Air Pressure Profiles

Description: Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are … more
Date: May 29, 1953
Creator: Sobolewski, Adam E.; Miller, Robert R. & McAulay, John E.
Partner: UNT Libraries Government Documents Department
open access

Stability of bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases

Description: Memorandum presenting an investigation of the stability of several bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases. Free-drop tests were made in the vertical 20-foot free-spinning tunnel to determine the behavior of the various bodies in descent.
Date: January 29, 1953
Creator: Scher, Stanley H. & Bowman, James S., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at Transonic Speeds of a Forward-Located Underslung Air Inlet on a Body of Revolution

Description: Report presenting an investigation in the transonic tunnel to determine the flow phenomena, pressure recovery, and external drag of a forward-located underslung air scoop mounted on a basic body of revolution with fineness ratio 11, which when cut off to provide an exit for the internal flow had a fineness ratio of 8. Results regarding the surface pressure distributions, drag, lift and pitching moment, and flow into the inlet on the modified model are provided.
Date: January 29, 1953
Creator: Pierpont, P. Kenneth & Braden, John A.
Partner: UNT Libraries Government Documents Department
open access

Minimum Spark-Ignition Energies of 12 Pure Fuels at Atmospheric and Reduced Pressure

Description: Memorandum presenting minimum spark-ignition energies for 12 pure fuels measured at reduced pressure, and the data obtained were extrapolated to 1 atmosphere. Some of the fuels investigated included normal and cycloparaffins, olefins, carbon disulfide, and oxygenated compounds such as alcohol, ether, propylene oxide, and tetrahydropyran.
Date: October 29, 1953
Creator: Metzler, Allen J.
Partner: UNT Libraries Government Documents Department
open access

Some torsional-damping measurements of laminated beams as applied to the propeller stall-flutter problem

Description: The structural damping in the torsion mode of vibration of a series of untwisted, laminated thin beams simulating propeller blades is presented. The number of lamination were varied, as well as the bonding material and the method of joining lamination. Application of the data to the calculation of the minimum flutter speed of thin propeller blades indicates that appreciable gains in the minimum flutter speed may be obtained for laminated blades using a Cycleweld bond.
Date: April 29, 1953
Creator: Heath, Atwood R., Jr.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at High Subsonic Speeds of a Spoiler-Slot Deflector Combination on an NACA 65A006 Wing With Quarter-Chord Line Swept Back 32.6 Degrees

Description: Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the lateral control characteristics of a wing-fuselage combination with the wing quarter-chord line swept back 32.6 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 section. Results regarding yawing-moment characteristics, spoiler-slot-deflector testing, and rolling-moment coefficient are provided.
Date: May 29, 1953
Creator: Vogler, Raymond D.
Partner: UNT Libraries Government Documents Department
open access

Performance of a Normal-Shock Scoop Inlet with Boundary-Layer Control

Description: Memorandum presenting tests made on a normal-shock inlet mounted as a scoop on a flat plate on which a turbulent boundary layer was generated. A boundary-layer-removal scoop was provided between the inlet and the plate and various amounts of the boundary layer were removed. Results regarding the main inlet, boundary-layer scoop, and an evaluation of results are provided.
Date: June 29, 1953
Creator: Frazer, Alson C. & Anderson, Warren E.
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of the Zero-Lift-Drag Characteristics of Symmetrical Blunt-Trailing-Edge Airfoils at Mach Numbers From 2.7 to 5.0

Description: Report presenting an investigation of the zero-lift-drag characteristics of nine symmetrical airfoils at a range of Mach and Reynolds numbers. Results regarding pressure and force data are also provided.
Date: April 29, 1953
Creator: Syvertson, Clarence A. & Gloria, Hermilo R.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of the effects of plan-form taper on the aerodynamic characteristics of symmetrical unswept wings of varying aspect ratio

Description: Report presenting an investigation to determine the effects of plan-form taper on the aerodynamic characteristics of a series of symmetrical, unswept wings with thicknesses of 8-percent chord. The wings were tested with four different bodies of revolution over a range of Mach numbers. Results regarding the lift, drag, pitching-moment, lift-curve slope, lift-drag ratio, and pitching-moment curve are provided.
Date: May 29, 1953
Creator: Allen, Edwin C.
Partner: UNT Libraries Government Documents Department
open access

Effects of High Degrees of Biaxial Stretch Forming on Crazing and Other Properties of Acrylic Plastic Glazing

Description: Memorandum presenting an investigation of the effects of higher degrees of forming in biaxial stretch-forming of polymethyl methacrylate to about 50-percent strain. Sheets of commercial cast polymethyl methacrylate were hot-stretched approximately 100 and 150 percent, respectively, and tests were conducted on this material and on unstretched cotton material. Results regarding the standard tensile tests, stress-solvent crazing, surface abrasion tests, and x-ray diffraction patterns are provided.
Date: May 29, 1953
Creator: Wolock, I.; Axilrod, B. M. & Sherman, M. A.
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of the effect of fences and balancing tabs on the hinge-moment characteristics of a tip control on a 60 degree delta wing at Mach number 1.61

Description: Report presenting an investigation at Mach number 1.61 of the effects of chordwise fences and attached tabs on the hinge-moment characteristics of a half-delta tip control mounted on a 60 degree delta wing. Testing occurred over a range of angles of attack and control deflection. Results indicated that, in general, the effect of fences was to improve the linearity of hinge-moment curves and increase the negative values of slope parameters of hinge moment against control deflection and angle of … more
Date: May 29, 1953
Creator: Czarnecki, K. R. & Lord, Douglas R.
Partner: UNT Libraries Government Documents Department
open access

Effective Thermal Conductivities of Magnesium Oxide Stainless Steel, and Uranium Oxide Powders

Description: Memorandum presenting testing conducted to determine the conductivity of magnesium oxide, stainless steel, and uranium oxide powders in various gases at a range of temperatures. Results regarding the experimental effective conductivities, comparison of analytical and experimental results, and effect of pressure on conductivity are provided.
Date: October 29, 1953
Creator: Eian, C. S. & Deissler, R. G.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Aileron Effectiveness as Determined by Force Tests and Visual-Flow Observations on a 52 Degree Sweptback Wing With and Without Chord-Extensions

Description: The results of an investigation of the effects of leading-edge chord-extensions and extensible leading-edge flaps on the low-speed aileron characteristics of a 52 degrees sweptback wing with circular-arc airfoil sections are presented. A description and illustrations of the vortex flow as it passes over the wing are included. The investigation was conducted at Reynolds numbers of 5.5 times 10(exp 6) and 1.3 times 10(exp 6) and corresponding Mach numbers of 0.11 and 0.065 for an angle-of-attack … more
Date: April 29, 1953
Creator: Cancro, Patrick A.
Partner: UNT Libraries Government Documents Department
open access

Altitude investigation of XJ34-WE-32 engine performance without electronic control

Description: From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."
Date: May 29, 1953
Creator: Bloomer, Harry E.; Walker, William J. & Pantages, George L.
Partner: UNT Libraries Government Documents Department
open access

The Aerodynamic Characteristics at Transonic Speeds of an All-Movable, Tapered, 45 Degree Sweptback, Aspect-Ratio-4 Tail Deflected About a Skewed Hinge Axis and Equipped with an Inset Unbalancing Tab

Description: From Introduction: "The present investigation presents the lift and moment characteristics of an aspect-ratio-4.0 tail, sweptback 45^o at the quarter-chord line and pivoted about an axis sweptback 55.5^o and passing through the leading edge of the root-chord line."
Date: September 29, 1953
Creator: Watson, James M.
Partner: UNT Libraries Government Documents Department
open access

A Theoretical Study of the Effect of Control-Deflection and Control-Rate Limitations on the Normal Acceleration and Roll Response of a Supersonic Interceptor

Description: Memorandum presenting a theoretical study of the effect of limiting the deflection and rate of deflection of the control surface on the normal acceleration and roll response to step commands for a representative, automatically controlled, supersonic, tailless interceptor. Results regarding pitch, roll, and some general comments are provided.
Date: April 29, 1953
Creator: Matthews, Howard F. & Schmidt, Stanley F.
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Root on a 45 Degree Sweptback Wing and Body Configuration

Description: Report presenting the zero-lift drag of a sweptback wing and body configuration with nacelles as determined by flight tests of rocket-propelled models at Mach numbers 0.8 to 1.3. Results regarding pressure recovery are also provided.
Date: September 29, 1953
Creator: Hoffman, Sherwood & Wolff, Austin L.
Partner: UNT Libraries Government Documents Department
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