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De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding

Description: Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.
Date: May 25, 1953
Creator: Ruggeri, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Impingement of Water Droplets on NACA 65(1)-208 and 65(1)-212 Airfoils at 4 Degrees Angle of Attack

Description: "The trajectories of droplets in the air flowing past NACA 65(1)-208 airfoil and an NACA 65(1)-212 airfoil, both at an angle of attack of 4 degrees, were determined. The amount of water in droplet form impinging on the airfoils, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface affected were calculated from the trajectories and are presented. The amount, extent, and rate of impingement of the NACA 65(1)-208 airfoil are compared with the re… more
Date: May 1953
Creator: Brun, Rinaldo J.; Gallagher, Helen M. & Vogt, Dorothea E.
Partner: UNT Libraries Government Documents Department
open access

Water-landing investigation of a flat-bottom v-step model and comparison with a theory incorporating planing data

Description: Report presenting testing of a flat-bottom V-step model with a beam loading of 4.6 subjected to fixed-trim impacts in smooth water. Testing occurred at three different trim angles and a range of initial flight-path angles. Data were obtained as time histories of draft, vertical velocity, and vertical acceleration. The results are presented as plots of nondimensional lift, draft, vertical velocity, and time against flight-path angle at contact.
Date: May 1953
Creator: Miller, Robert W.
Partner: UNT Libraries Government Documents Department
open access

Strength analysis of stiffened thick beam webs with ratios of web depth to web thickness of approximately 60

Description: "The results of an experimental investigation of the strength of plane diagonal-tension webs with ratios of web depth to web thickness of about 60 are presented. An analysis of the beam indicated that the methods of strength analysis presented in NACA TN 2661 are applicable to beams with flanges symmetrically arranged with respect to the web if the portal-frame effect is taken into account" (p. 1).
Date: May 1953
Creator: Levin, L. Ross
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Experimental Aerodynamic Loading on a Model Helicopter Rotor Blade

Description: Note presenting pressure distributions measured on a model helicopter rotor blade under hovering and simulated forward-flight conditions. Pressure were recorded at advance ratios of 0.10, 0.22, 0.30, 0.40, and 0.50 for a zero-offset flapping-hinge rotor and at 0.10, 0.22, 0.30, 0.45, 0.60, 0.80, and 1.0 for a lifting rotor with a flapping-hinge offset of 13 percent.
Date: May 1953
Creator: Meyer, John R., Jr. & Falabella, Gaetano, Jr.
Partner: UNT Libraries Government Documents Department
open access

A new shadowgraph technique for the observation of conical flow phenomena in supersonic flow and preliminary results obtained for a triangular wing

Description: Report presenting a new shadowgraph technique for the observation of conical flow phenomena in supersonic flow. The particular advantage of this technique is that it permits observation of the conical flow phenomena in a plane normal or nearly normal to the axis of propagation. Results regarding cones and triangular wings are provided.
Date: May 1953
Creator: Love, Eugene S. & Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Lateral Control Near the Stall: Flight Investigation With a Light High-Wing Monoplane Tested With Various Amounts of Washout and Various Lengths of Leading-Edge Slot

Description: Note presenting flight tests made with a typical light airplane to investigate possibilities for obtaining reliable control at low flight speeds. An attempt was made to find a configuration that would provide sufficient elevator control for a three-point landing under the most critical condition and that would also have insufficient elevator control to exceed the angle of attack at which reliable lateral control is obtained in flight under all of the center-of-gravity and power conditions.
Date: May 1953
Creator: Weick, Fred E.; Sevelson, Maurice S.; McClure, James G. & Flanagan, Marion D.
Partner: UNT Libraries Government Documents Department
open access

A variable-frequency light synchronized with a high-speed motion-picture camera to provide very short exposure times

Description: Report discussing a new high-speed photographic technique, which employs a variable-frequency light synchronized with a commercially available 16-millimeter high-speed motion-picture camera without appreciable alterations to the camera. The technique is described and results obtained by the technique of photographing the flow past models in a wind tunnel with the schileren method of flow visualization are presented.
Date: May 1953
Creator: Lindsey, Walter F. & Burlock, Joseph
Partner: UNT Libraries Government Documents Department
open access

Effect of high bulk temperatures on boundary lubrication of steel surfaces by synthetic fluids

Description: "High operating temperatures of new and projected turbine engines require that synthetic fluids be used as lubricants, because these fluids have better thermal stability and viscosity-temperature characteristics than petroleum oils have. An experimental study was conducted to learn the effect of high lubricant bulk temperatures on the boundary lubricating effectiveness of various types of synthetic fluid" (p. 1).
Date: May 1953
Creator: Murray, S. F.; Johnson, Robert L. & Bisson, Edmond E.
Partner: UNT Libraries Government Documents Department
open access

The Creep of Single Crystals of Aluminum

Description: The creep of single crystals of high-purity aluminum was investigated in the range of temperatures from room temperature to 400 F and at resolved-shear-stress levels of 200, 300, and 400 psi. The tests were designed in an attempt to produce data regarding the relation between the rate of strain and the mechanism of deformation. The creep data are analyzed in terms of shear strain rate and the results are discussed with regard to existing creep theories.
Date: May 1953
Creator: Johnson, R. D.; Shober, F. R. & Schwope, A. D.
Partner: UNT Libraries Government Documents Department
open access

Combined-Stress Fatigue Strength of 76S-T61 Aluminum Alloy With Superimposed Mean Stresses and Corrections for Yielding

Description: Note presenting fatigue data for 76S-T61 aluminum alloy for several combinations of bending and torsion with both alternating and mean stresses. The literature on the effect of combined stress and of mean stress in fatigue is reviewed and the results of the present series are compared with those of various theories. Results regarding fatigue data, fatigue fractures, and static tests are provided.
Date: May 1953
Creator: Findley, William N.
Partner: UNT Libraries Government Documents Department
open access

Static force-deflection characteristics of six aircraft tires under combined loading

Description: Report presenting static force-deflection tests on six aircraft tires ranging in size and ply rating. Testing included the vertical loading of all six tire specimens and, for five of the tire specimens, combined vertical loading and side loading and combined vertical loading and torsional loading.
Date: May 1953
Creator: Horne, Walter B.
Partner: UNT Libraries Government Documents Department
open access

Deflection of Delta Wings Having a Carry-Through-Bay Chord Smaller than the Wing Root Chord

Description: Note presenting experimentally determined influence coefficients for the deflection of two solid delta wings - one wing of constant thickness and the other of constant thickness ratio - with a carry-through-bay chord smaller than the wing root chord. The experimental tip-load deflections of the constant-thickness wing exceed those computed by the present theory by approximately 15 to 20 percent at the tip.
Date: May 1953
Creator: Peters, Roger W. & Stein, Manuel
Partner: UNT Libraries Government Documents Department
open access

Pressure distributions about finite wedges in bounded and unbounded subsonic streams

Description: An analytical investigation of incompressible flow about wedges was made to determine effects of tunnel-wedge ratio and wedge angle on the wedge pressure distributions. The region of applicability of infinite wedge-type velocity distribution was examined for finite wedges. Theoretical and experimental pressure coefficients for various tunnel-wedge ratios, wedge angles, and subsonic Mach numbers were compared.
Date: May 1953
Creator: Donoughe, Patrick L. & Prasse, Ernst I.
Partner: UNT Libraries Government Documents Department
open access

The attenuation characteristics of four specially designed mufflers tested on a practical engine setup

Description: Attenuation characteristics of four different resonator mufflers were determined in both cold tests and engine field tests and compared with the theoretical calculations. These mufflers were specifically designed for a helicopter. Engine-exhaust sound pressures, temperatures, and noise levels from the helicopter were measured. The experimental muffler cold tests indicated close a agreement with theory, whereas the engine tests indicated some discrepancies. Test results show the usefulness of th… more
Date: May 1953
Creator: Stokes, George M. & Davis, Don D., Jr.
Partner: UNT Libraries Government Documents Department
open access

Combustion instability in an acid-heptane rocket with a pressurized-gas propellant pumping system

Description: Report presenting results of experimental measurements of low-frequency combustion instability of a 300-pound-thrust acid-heptane rocket engine as compared with the trends predicted by an analysis of combustion instability in a rocket engine. Results regarding the chugging frequency, combustion time delay, effect of rocket combustion-chamber characteristic length, effect of throttling, effect of injection velocity, effect of oxidant-fuel ratio, variation of chugging frequency with amplitude of … more
Date: May 1953
Creator: Tischler, Adelbert O. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department
open access

Calculated spanwise lift distributions, influence functions, and influence coefficients for unswept wings in subsonic flow

Description: Spanwise lift distributions have been calculated for nineteen unswept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were aerodynamic influence coefficients which pertain to a certain definite set of stations along the span, and several methods are presented for calculating aerodynamic influence func… more
Date: May 5, 1953
Creator: Diederich, Franklin W. & Zlotnick, Martin
Partner: UNT Libraries Government Documents Department
open access

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96

Description: From Summary: "An investigation of the characteristics of a full-scale supersonic-type propeller has been made in the Langley 16-foot transonic tunnel with the 6000-horsepower propeller dynamometer. The tests covered a range of blade angles from 20.2 degrees to 60.2 degrees at forward Mach numbers up to 0.96. The results showed that envelope efficiency at an advance ratio of 2.8 decreased from 86 percent to 72 percent when the forward Mach number was increased from 0.70 to 0.96."
Date: May 18, 1953
Creator: Evans, Albert J. & Liner, George
Partner: UNT Libraries Government Documents Department
open access

Time-History Data of Maneuvers Performed by a Republic F84G Airplane During Squadron Operational Training

Description: Preliminary results of one phase of a control-motion study program involving several jet fighter-type airplanes are presented in time-history form and are summarized as maximum measured quantities plotted against indicated airspeed. The results pertain to approximately 1,000 maneuvers performed by a Republic F-84G jet-fighter airplane during squadron operational training. The data include most tactical maneuvers of which the F-84G airplane is capable. Maneuvers were performed at pressure altitu… more
Date: May 18, 1953
Creator: Hamer, Harold A. & Mayo, Alton P.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the rolling stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from … more
Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department
open access

Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model

Description: Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data.
Date: May 14, 1953
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department
open access

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. The two compressor modifications investigated included twisting rotor blades to change blade section angles and inserting new stator diaphragms with different blade angles. Results regarding the effect of surge limit on engine performance, performance map of original compressor with mixer, effect of blade modifications on surge line, effect of mixe… more
Date: May 20, 1953
Creator: Finger, Harold B.; Essig, Robert H. & Conrad, E. William
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
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