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Single-Cylinder Oil-Control Tests of Porous Chrome Plated Cylinder Barrels for Radial Air-Cooled Engines

Description: Report presenting a series of single-cylinder engine tests run to determine a satisfactory method of reducing oil consumption in radial air-cooled engines with flat-face compression rings as standard parts and equipped with cylinder barrels salvaged by porous chrome plating. Testing was conducted using porous chrome-plated cylinders with straight and choke bores with standard flat-face compression rings.
Date: January 1946
Creator: Johnson, Robert L. & Swikert, Max
Partner: UNT Libraries Government Documents Department

Ditching Tests of a 1/8-Scale Model of the Navy SB2c-1 Airplane (Army A-25) in Langley Tank Number 2 and on an Outdoor Catapult

Description: Report presenting testing to determine the best way to land the SB2C-1 airplane in calm and rough water and to determine its probable ditching performance. The behavior of the model was determined by making visual observations and by recording the maximum longitudinal decelerations and by taking motion pictures of the ditchings. Results regarding the effect of flaps, attitude, weight, a wing-low landing, effect of simulated damage, effect of tail wheel, ditching aids, and seaway are provided.
Date: January 1946
Creator: Jarvis, George A.
Partner: UNT Libraries Government Documents Department

Air-Flow and Performance Characteristics of Engine-Stage Supercharger of a Double-Row Radial Aircraft Engine 2: Effect of Design Variables

Description: Report presenting an investigation to determine the effect of the location of the diffuser vanes with respect to the supercharger outlets and the effect of flow conditions at the impeller inlet on the air-flow distribution in the outlets of the engine-stage supercharger of an 18-cylinder double-row radial aircraft engine. The effect of flow conditions at the impeller inlet was investigated by distorting the flow at the inlet and noting the effect in the supercharger outlets. Results regarding the diffuser effect and inlet effect are provided.
Date: August 1946
Creator: Baas, Edmund J. & Dugan, Paul D.
Partner: UNT Libraries Government Documents Department

Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter

Description: From Introduction: "The research program included clean-up tests (unpublished data) and stability and control tests (reference 1) made in the NACA Langley full-scale tunnel. An investigation of the aerodynamic characteristics of the power-plant installation in the Cleveland altitude wind tunnel is discussed in this report."
Date: February 1946
Creator: Preston, G. Merritt; Black, Fred O., Jr. & Jagger, James M.
Partner: UNT Libraries Government Documents Department

Effect of a low-loss air valve on performance of a 22-inch-diameter pulse-jet engine

Description: Report presenting the performance of a 22-inch-diameter pulse-jet engine using a net of low-loss modified air valves at ram pressures equivalent to simulated flight speeds. Results regarding combustion-air weight flow, flight thrust, maximum combustion-chamber pressure, specific fuel consumption, pressure cycle, and valve life are provided.
Date: June 1946
Creator: Bressman, Joseph R.
Partner: UNT Libraries Government Documents Department

Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane

Description: From Introduction: "An investigation of the power-plant installation of a single-engine torpedo-bomber-type airplane has been conducted in the NACA Cleveland altitude wind tunnel at the request of the Bureau of Aeronautics, Navy Department. A similar investigation was previously conducted on a three-tenths scale mock-up of the forward portion of the fuselage of this airplane in the Langley 20-foot tunnel. (See reference 1)."
Date: June 1946
Creator: Palter, Herman
Partner: UNT Libraries Government Documents Department

Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel

Description: From Summary: "A 1/7 scale semispan model of the XB-35 airplane was tested in the Langley 10 foot pressure tunnel, primarily for the purpose of investigating the effectiveness of a leading-edge slot for alleviation of stick-fixed longitudinal instability at high angles of attack caused by early tip stalling and a device for relief of stick-free instability caused by elevon up-floating tendencies at high angles of attack. Results indicated that the slot was not adequate to provide the desired improvement in stick-fixed stability."
Date: January 16, 1946
Creator: Teplitz, Jerome; Kayten, Gerald G. & Cancro, Patrick A.
Partner: UNT Libraries Government Documents Department

An analysis of the indications of the University of Chicago airborne turbulence indicator in gusty air

Description: From Introduction: "The present report has been prepared to discuss the indications obtained from the University of Chicago turbulence indicator in relation to simultaneous measurement of atmospheric gustiness made by the NACA, which are summarized herein."
Date: August 1946
Creator: Tolefson, H. B. & Pratt, K. G.
Partner: UNT Libraries Government Documents Department

A Preliminary Investigation of the Icing Characteristics of a Large Rectangular-Throat Pressure-Type Carburetor

Description: Report discussing the icing characteristics of a rectangular-throat pressure-type carburetor. Serious ice was not found to form under the conditions of this particular test, although visible ice and frost formed in certain areas.
Date: July 1946
Creator: Chapman, Gilbert E.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling

Description: Data are presented of the flow conditions in the vicinity of an NACA D sub S -type cowling. Tests were made of a 1/2 scale-nacelle model at inlet-velocity ratios ranging from 0.23 to 1.02 and angles of attack from 6 deg to 10 deg. The velocity and direction of flow in the vertical plane of symmetry of the cowling were determined from orifices and tufts installed on a board aligned with the flow. Diagrams showing velocity ratio contours and lines of constant flow angles are given.
Date: August 1946
Creator: Bryant, Rosemary P. & Boswinkle, Robert W., Jr.
Partner: UNT Libraries Government Documents Department

Single-Cylinder Engine Tests of Porous Chrome-Plated Cylinder Barrels With Special Bore Coatings for Radial Air-Cooled Engines

Description: Report discussing a series of single-cylinder engine tests to determine the effect of special surface coatings in porous chrome-plated cylinder barrels on oil consumption and ring wear. The coating materials were selected for their bearing and lubrication properties and on their applicability to processing. The surface coatings tested were lead overplates, silver overplates, and colloidal graphite base paint.
Date: January 1946
Creator: Johnson, Robert L. & Anderson, Roy I.
Partner: UNT Libraries Government Documents Department

A Preliminary Theoretical Study of Helicopter-Blade Flutter Involving Dependence Upon Coning Angle and Pitch Setting

Description: "A preliminary analysis has been made of the conditions of stability of free oscillations of a hinged rotor in hovering flight. The case analyzed is a rotor with hinges allowing freedom in flapping and lagging and having a completely reversible cyclic pitch-control system, so that a twisting moment on a blade moves the control stick without hindrance from spring or friction constraint. The principal results of this study are presented in the form of a stability chart" (p. 1).
Date: July 1946
Creator: Coleman, Robert P.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of Two NACA Low-Drag Airfoil Sections Equipped With Slotted Flaps and a Plain NACA Low-Drag Airfoil Section for XF6U-L Airplane

Description: Report discussing the results of testing to determine the aerodynamic characteristics of three NACA-designed airfoil sections, some with flaps equipped. The tests included determination of the aerodynamic characteristics of the airfoils in smooth conditions and with standard roughness applied to the leading edge. Lift tests were also carried out at a range of flap deflections.
Date: January 1946
Creator: Loftin, Lawrence K., Jr. & Rice, Fred J., Jr.
Partner: UNT Libraries Government Documents Department

Static-Thrust Investigation of Full-Scale PV-2 Helicopter Rotors Having NACA 0012.6 and 23012.6 Airfoil Sections

Description: An investigation was conducted to compare the performance of two 25-ft-diam rotors which had identical dimensions and were similar in construction but different in blade airfoil-sections. Tests were conducted at indicated blade pitch angles from 3 degrees to 11.5 degrees and rotor speeds of 200, 290, and 371 rpm. The 23012.6 rotor required 2 percent less power to hover than the 0012.6. At thrust coefficients above design, the performance of the 23012.6 became better than the 0012.6 rotor.
Date: May 1946
Creator: Lipson, Stanley
Partner: UNT Libraries Government Documents Department

Some Notes on the Effects of Jet-Exit Design on Static Longitudinal Stability

Description: Report discussing several types of jet-exit designs, including normal, beveled, and unsymmetrical shapes, and their effect on the stability characteristics of the aircraft. No deviation of the jet center line from its exposed path is likely to be obtained if a jet exist is used that is normal to the flow. Having a tilted or asymmetrical exit was found to adversely affect the stability of the aircraft.
Date: May 1946
Creator: Gillis, Clarence L. & Weil, Joseph
Partner: UNT Libraries Government Documents Department

Tests of the Jet-Motor Air-Intake Duct System on a 1/4-Scale Stub-Wing Model of a Pursuit-Type Airplane

Description: Report discussing the characteristics of the jet-motor air-intake duct system for a pursuit-type airplane with modifications to the duct system. Details of its effects on the Mach number, high pressure recovery, drag, and simplicity of the system are provided. Problems regarding the flow condition through the ducts and some potential modifications to prevent further issues are also described.
Date: May 1946
Creator: Hanson, Frederick H., Jr.
Partner: UNT Libraries Government Documents Department

Test-Stand Investigation of Cooling Characteristics and Factors Affecting Temperature Distribution of a Double-Row Aircraft Engine

Description: Report presenting testing of a double-row radial air-cooled engine to investigate overall cooling characteristics and to analyze what variations in temperature distribution were caused by variations in cooling-air pressure drop, power, and fuel-air ratio. Testing occurred over a range of engine powers.
Date: March 1946
Creator: Sipko, Michael A.; Hickel, Robert O. & Jones, Robert J.
Partner: UNT Libraries Government Documents Department

Tests of a 1/7-Scale Powered Model of the Kaiser Tailless Airplane in the Langley Full-Scale Tunnel

Description: Report discussing testing of a model of the Kaiser tailless airplane in order to determine its general aerodynamic characteristics and the probable stability and control characteristics. Only the results of the tests are presented in this report; the estimated flying qualities are in a separate report. Information about the lift, stall, drag, elevator effectiveness and hinge moments, rudder effectiveness and hinge moments, aileron effectiveness and hinge moments, and characteristics in yaw is included.
Date: March 1946
Creator: Brewer, C. W. & Rickey, E. A.
Partner: UNT Libraries Government Documents Department

Tests of Cast Aluminum-Alloy Mixed-Flow Impellers

Description: "A machined mixed-flow centrifugal impeller of a relatively complex passage shape was used as a pattern to cast a number of aluminum-alloy impellers from two aluminum-base alloys (designated alloys 1 and 2) by the 'lost wax' process. An investigation was conducted to determine whether these cast impellers, could be considered satisfactory for use in compressors. The investigation included preliminary examination, physical tests, metallurgical examination, and performance tests" (p. 1).
Date: April 1946
Creator: Douglas, John E. & Schwartz, Irving R.
Partner: UNT Libraries Government Documents Department

Correlation of Mixture Temperature Data Obtained From Bare Intake-Manifold Thermocouples

Description: "A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and test stands other than the NACA" (p. 1).
Date: January 1946
Creator: White, H. Jack & Gammon, Goldie L.
Partner: UNT Libraries Government Documents Department

The Effect of Liquid and Ice Particles on the Erosion of a Supercharger-Inlet Cover and Diffuser Vanes

Description: Report discussing the results of accelerated erosion tests to determine the separate effects of the passage of fuel, water, and ice particles through a supercharger. Recommendations for preventing erosion are provided, including materials choice and joint design.
Date: June 1946
Creator: Rollin, Vern G.
Partner: UNT Libraries Government Documents Department

Efficiency of a Radial-Flow Exhaust-Gas Turbosupercharger Turbine With a 12.75-Inch Tip Diameter

Description: Report discussing the effects of various inlet pressures, inlet temperatures, wheel speeds, pressure ratios, and cooling-air flows on the performance of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter. Information about efficiency is provided for a given blade-to-jet speed ratio.
Date: July 1946
Creator: Coulter, Earl E.; Larkin, Robert G. & Gabriel, David S.
Partner: UNT Libraries Government Documents Department

An Evaluation of the Knock-Limited Performance of Triptane

Description: Report discussing an investigation of the knock-limited performance of triptane in F-3 and F-4 rating engines, two full-scale air-cooled aircraft cylinders, and flight tests on a full-scale multicylinder engine. Information about the lead susceptibility and effect of engine operating conditions is also provided.
Date: March 1946
Creator: Barnett, Henry C.
Partner: UNT Libraries Government Documents Department

The Effect of Increase in Combustion-Air Inlet Temperature From 80 to 130 F on the Sea-Level Performance of a 22-Inch-Diameter Pulse-Jet Engine

Description: Report discussing testing on 22 inch-diameter pulse-jet engines to determine the effect on performance of a change in combustion-air temperature from approximately 80 degrees to 130 degrees. The effects on jet thrust, combustion-air flow, and engine thrust are described.
Date: July 1946
Creator: Valerino, Michael F.; Essig, Robert H. & Hughes, Richard F.
Partner: UNT Libraries Government Documents Department