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A Flight Investigation of the Effect of Mass Distribution and Control Setting on the Spinning of the XN2Y-1 Airplane

Description: "The investigation of the effect of mass distribution on the spinning of airplanes initiated with tests on the NY-1 airplane has been continued by tests on another airplane in order to increase the scope of the information and to observe particularly the behavior of an airplane that shows considerable change in sideslip angle for its various conditions of spinning. The XN2Y-1 naval training biplane was used for the present tests in which changes of ballast along the longitudinal and lateral axes and changes of aileron, stabilizer, and elevator settings were made. The effects of these changes on the steady spin were measured in flight' (p. 185).
Date: January 10, 1934
Creator: Scudder, N. F.
Partner: UNT Libraries Government Documents Department
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The Effect of Water Vapor on Flame Velocity in Equivalent Carbon Monoxide and Oxygen Mixtures

Description: This report presents the results of an investigation to study the effect of water vapor upon the spatial speed of flame in equivalent mixtures of carbon monoxide and oxygen at various total pressures from 100 to 780 mm.hg. These results show that, within this pressure range, an increase in flame speed is produced by increasing the mole fraction of water vapor at least as far as saturation at 25 degrees c., and that the rate of this increase is greater the higher the pressure. It is evident that water vapor plays an important part in the explosive oxidation of carbon monoxide; the need for further experimental evidence as to the nature of its action is indicated.
Date: January 10, 1935
Creator: Fiock, Ernest F. & King, H. Kendall
Partner: UNT Libraries Government Documents Department
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The Soap-Bubble Method of Studying the Combustion of Mixtures of Carbon Monoxide and Oxygen

Description: This investigation is a detailed description of the soap-bubble, or constant-pressure, method as applied to the explosive oxidation of carbon monoxide. A series of values of the speed of flame in space in various mixtures of CO and O2 containing a constant percentage of water vapor was obtained by the constant-volume method. These results served as a guide in the perfection of the soap-bubble method.
Date: January 10, 1935
Creator: Fiock, Ernest F. & Roeder, Carl H.
Partner: UNT Libraries Government Documents Department
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A study of the torque equilibrium of an autogiro rotor

Description: From Summary: "Two improvements have been made in the method developed in NACA Reports nos. 487 and 591 for the estimation of the inflow velocity required to overcome a given decelerating torque in an autogiro rotor. At low tip-speed ratios, where the assumptions necessary for the analytical integrations of the earlier papers are valid, the expressions therein derived are greatly simplified by combining and eliminating terms with a view of minimizing the numerical computations required. At high tip-speed ratios, by means of charts based on graphical integrations, errors inherent in the assumptions associated with the analytical method are largely eliminated."
Date: January 10, 1938
Creator: Bailey, F. J., Jr.
Partner: UNT Libraries Government Documents Department
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Preliminary wind-tunnel investigation of an NACA 23012 airfoil with various arrangements of venetian-blind flaps

Description: Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of venetian-blind flaps to determine the aerodynamic section characteristics as affected by the over-all flap chord, the chords of the slats used to form the flap, the slat spacing, the number of slats and the position of the flap with respect to the wing. Complete section data are given in the form of graphs for all the combinations tested.
Date: January 10, 1939
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Partner: UNT Libraries Government Documents Department
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Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Fairchild Lark Pilotless-Aircraft Configuration. Static Longitudinal Stability of Models with Wing Flap Deflections of 0 Deg and 15 Deg, TED No. NACA 2387

Description: From flight tests of 0.5-scale models of the Fairchild Lark pilotless aircraft conducted at the flight test station of the Pilotless Aircraft Research Division at Wallops Island, Va., some evaluations of the static longitudinal stability were obtained by analysis of the short-period oscillations induced by the abrupt movement of the rudder elevators. The analysis shows that for the Lark configuration with wing flap deflections of 0 degrees and 15 degrees the static longitudinal stability decreases slightly up to the critical Mach number and than as the Mach number increases further the stability increases greatly.
Date: January 10, 1947
Creator: Stone, David G.
Partner: UNT Libraries Government Documents Department
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Interference Method for Obtaining the Potential Flow Past an Arbitrary Cascade of Airfoils

Description: "A procedure is presented for obtaining the pressure distribution on an arbitrary airfoil section in cascade in a two-dimensional, incompressible, and nonviscous flow. The method considers directly the influence on a given airfoil of the rest of the cascade and evaluates this interference by an iterative process, which appeared to converge rapidly in the cases tried (about unit solidity, stagger angles of 0 degree and 45 degrees). Two variations of the basic interference calculations are described" (p. 1).
Date: January 10, 1947
Creator: Katzoff, S.; Finn, Robert S. & Laurence, James C.
Partner: UNT Libraries Government Documents Department
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Heat-transfer and boundary-layer transition on a heated 20 degree cone at a Mach number of 1.53

Description: Heat-transfer data from supersonic wind-tunnel tests of a heated 20 degree cone are compared with theoretical results obtained by the method for determining the convective heat transfer in laminar boundary layers in a compressible fluid developed by Hantzche and Wendt and with the method presented in NACA TN No. 1300. The experimental data are also compared with the results obtained by Eber at the Kochel Laboratory in Germany and it is found that Eber's results correspond to those obtained with a turbulent boundary layer on the cone. The results provide a qualitative verification of the effect of heat transfer on laminar boundary-layer stability that has been predicted theoretically by Lees in NACA TN No. 1360.
Date: January 10, 1949
Creator: Scherrer, Richard; Wimbrow, William R. & Gowen, Forrest E.
Partner: UNT Libraries Government Documents Department
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Preparation of Ductile Zirconium: Progress Report for December 1949

Description: Report discussing progress made by the National Research Corporation in developing preparation of ductile zirconium for the month of December, 1949.
Date: January 10, 1950
Creator: DiPietro, W. O.; Findlay, G. R. & Stauffer, R. A.
Partner: UNT Libraries Government Documents Department
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Production of Pi-Mesons in Lead by High Energy Proton Bombardment

Description: Our knowledge of the properties of mesons and their interactions with nuclei has come from two sources. Studies of cosmic ray phenomena provided the earliest information. The discovery that mesons may be produced artificially by bombardment of nuclei with radiations from high energy accelerators has, on the other hand, made it feasible to undertake a wide variety of investigations under more controlled conditions than is possible in cosmic ray experiments. In such experiments mesons have been produced by high-energy protons, alpha-particles and neutrons.
Date: January 10, 1950
Creator: Weissbluth, Mitchel
Partner: UNT Libraries Government Documents Department
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Conversion of Unh to UO$sub 3$. Terminal Report

Description: Experimental results indicate that the production of UO/sub 3/ by the continuous calcination process is practicable. (W.L.H.)
Date: January 10, 1951
Creator: Maness, R. F. & Clagett, F.
Partner: UNT Libraries Government Documents Department
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Conversion of UNH to UO3 : Terminal Report

Description: Feasibility of conversion of uranyl nitrate to uranium trioxide by the continuous addition of concentrated uranyl nitrate solution to hot, agitated UO3 powder.
Date: January 10, 1951
Creator: Maness, R. F. & Clagett, F.
Partner: UNT Libraries Government Documents Department
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Impact Extrusion of Uranium

Description: Uranium has been successfully impact extruded into typical cylindrical shapes of conventional design. Extrusion was carried out in the "gamma" region by heating cast uranium slugs to a temperature of approximately 1050 degrees C. Protection against oxidation was afforded by surrounding the slugs during heating with an inert atmosphere of argon gas. Impact extruded shapes possessed physical properties which are better than the properties of as-cast metal. Also, extruded shapes show a uniform internal structure with flow lines characteristic of commercial impact extruded pieces formed from other metals. Impact extrusion, as a fabricating processes for uranium, maybe applied successfully to produce complicated shapes or forms not practical by casting or where savings in metal and machining time is desired. The process would not appear to be commercial unless a large quantity of pieces was required.
Date: January 10, 1951
Creator: Hanks, G. S.; Jaynes, G. E.; Taub, J. M. & Doll, D. T.
Partner: UNT Libraries Government Documents Department
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Investigation of altitude starting and acceleration characteristics of J47 turbojet engine

Description: An investigation was conducted on an axial-flow-compressor type turbojet engine in the NACA Lewis altitude wind tunnel to determine the operational characteristics of several ignition systems, cross-fire tube configurations and fuel systems over a range of simulated flight conditions. The opposite-polarity-type spark plug provided the most satisfactory ignition. Increasing the cross-fire-tube diameter improved intercombustor flame propagation. At high windmilling speeds, accelerations to approximately 6200 rpm could be made at a preset constant throttle position. The use of a variable-area nozzle reduced acceleration time.
Date: January 10, 1951
Creator: Golladay, Richard L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
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Lateral-Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable-Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52

Description: Memorandum presenting an investigation of aileron effectiveness and dihedral effect for a wing-body combination with a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. The experimental value of aileron effectiveness at 0 degrees angle of attack was approximately 78 percent of the value predicted by linear theory, and the effectiveness decreased with increasing wing angle of attack.
Date: January 10, 1951
Creator: Scherrer, Richard & Dennis, David H.
Partner: UNT Libraries Government Documents Department
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Lateral Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52

Description: "Aileron effectiveness and dihedral effect were investigated for a wing-body combination having a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. At the Mach number of the tests, the Mach cone from the wing apex was almost coincident with the wing leading edge" (p. 1).
Date: January 10, 1951
Creator: Scherrer, Richard & Dennis, David H.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.60 to determine the effects of sweep and thickness on the longitudinal characteristics of a series of wing-body combinations with cambered wings with an aspect ratio of 3.5 and taper ratio of 0.2. The results show the effects of sweep, thickness, and the horizontal canard surface on the lift, drag, and pitching-moment coefficients and lift-drag ratios. The lift-curve slope, aerodynamic-center locations, maximum lift-drag ratios, lift coefficients for maximum lift-drag ratio, and drag-rise factor are presented.
Date: January 10, 1952
Creator: Robinson, Ross B. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Directional Behavior of a Swept Planing-Tail Hull

Description: "A qualitative investigation of the low-speed directional behavior of a swept planing-tail hull was made in the Langley tank no. 2 in still water and still air with the use of a free self-propelled model. The configuration was directionally unstable over a range of low speed. It was, however, directionally controllable at all speeds by use of the rudder and elevator. Several modifications that were investigated did not improve the controllability" (p. 1).
Date: January 10, 1952
Creator: Arabian, Donald D.
Partner: UNT Libraries Government Documents Department
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An Investigation of Propeller Vibrations Excited by Wing Wakes

Description: Report presenting an investigation of the principal variables affecting the excitation of a propeller for vibration at a frequency of twice propeller speed using a conventional propeller with solid aluminum-alloy blades operating in the wake of a wing. The drag of the wing and spacing between the flap trailing edge and propeller plane were all adjustable. Results regarding wing drag data, vibratory stresses, damping, and theoretical considerations of wake excited blade stresses are provided.
Date: January 10, 1952
Creator: Gray, W. H. & Solomon, William
Partner: UNT Libraries Government Documents Department
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Low-speed investigation of the effects of wing leading-edge modifications and several outboard fin arrangements on the static stability characteristics of a large-scale triangular wing

Description: Report presenting an investigation of a large-scale triangular wing with 60 degrees of leading-edge sweep and with 10-percent-thick circular-arc airfoil sections parallel to the plane of symmetry was made in the full-scale tunnel to determine the effects of wing leading-edge modifications and several outboard fin arrangements on the low-speed static stability characteristics. Results regarding static longitudinal stability characteristics and static lateral stability characteristics are provided.
Date: January 10, 1952
Creator: McLemore, H. Clyde
Partner: UNT Libraries Government Documents Department
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RDA DC-6 -- Design criteria for reactor water plant at Coyote Rapids site. Instruction letter number 1

Description: The design will be based on one reactor with a potential capacity of 1,300 megawatts. For the time being this reactor will be designated ``X``. The water plant will be designed to supply 100,000 gpm initially. The design shall provide, however, for the ultimate capacity of 140,000 gpm; i.e., underground process piping, space in river pump house, and other items which would be difficult to enlarge after initial construction, will be sized for the ultimate capacity and provision shall be made for future enlargement of filter plants, etc. to provide the required increase in capacity.
Date: January 10, 1952
Creator: Pilkey, O. H.
Partner: UNT Libraries Government Documents Department
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Small-scale transonic investigation of the effects of twist and camber on the aerodynamic characteristics of a 60 degrees 42' sweptback wing of aspect ratio 1.94

Description: Report presenting a small-scale investigation of two semispan wings with the same plan form in the high-speed 7- by 10-foot tunnel over a range of Mach numbers to determine the effects of twist and camber on the aerodynamic characteristics of a 60 degrees 42' sweptback wing of aspect ratio 1.94. Lift, drag, pitching moment, and root bending moment were obtained for the two wings investigated.
Date: January 10, 1952
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Partner: UNT Libraries Government Documents Department
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Weighting Factors for Radically Flattened Piles

Description: The following report calculates pile reactivity changes that result from different pile loadings where it is desirable to have available values of (flux)2 d(volume) for various flat zone radii. This information was found for a cylindrical pile having circular flat zones and an effective radius of 598 cm., by integrating over a cross sectional volume of one cm. thickness.
Date: January 10, 1952
Creator: Woodruff, R. W.
Partner: UNT Libraries Government Documents Department
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Hydrolysis of Uranium Tetra-Fluoride

Description: The following report provides tables that measure the pressure of hydrogen fluoride at given temperatures and the hydrolysis of uranium tetrafluoride.
Date: January 10, 1953
Creator: Bernhardt, Harvey A.
Partner: UNT Libraries Government Documents Department
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