National Advisory Committee for Aeronautics (NACA) - 39 Matching Results

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Preliminary Investigation of Effects of Alpha-Particle Bombardment on the Creep Rate of Aluminum

Description: Memorandum presenting a preliminary investigation to determine the effects of alpha-particle bombardment on the creep rate of aluminum wire at 400 degrees Fahrenheit. The alpha radiation from an 85-millicurie polonium source appeared to decrease slightly the creep rate of the aluminum.
Date: July 3, 1947
Creator: Kittel, J. Howard
Partner: UNT Libraries Government Documents Department
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Increase in Stable-Air-Flow Operating Range of a Mixed-Flow Compressor by Means of a Surge Inhibitor

Description: Report presenting an investigation of a surge inhibitor that was able to cause a considerable gain in stable-airflow operating range over the range of equivalent impeller tip speeds tested. While the inhibitor was designed to triple the stable-airflow operating range, it increased it more than eight times its original value.
Date: April 3, 1947
Creator: Laskin, Eugene B. & Kofskey, Milton G.
Partner: UNT Libraries Government Documents Department
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Computed Performance of a Composite Engine Based on Experimental Data for a Single-Cylinder Conventional Aircraft Engine Converted to Compression-Ignition Operation

Description: Memorandum presenting a determination of the performance of a single-cylinder spark-ignition engine modified to operate on a compression-ignition cycle with a compression ratio of 8.0. Experimental data were obtained at an inlet-manifold pressure of 100 inches of mercury absolute, fuel-air ratios of 0.040 and 0.025, and engine exhaust pressures of 30 to 100 inches of mercury absolute. Results regarding single-cylinder-engine experimental data and full-scale-engine calculations are provided.
Date: February 3, 1947
Creator: McCoy, J. Arnold & Szel, Frank
Partner: UNT Libraries Government Documents Department
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Knock-limited power outputs from a CFR engine using internal coolants 3: four alkyl amines, three alkanolamines six amides, and eight heterocyclic compounds

Description: Report presenting investigations to determine the antiknock effectiveness of various additive-water solutions used as internal coolants in conjunction with AN-F-28, Amendment-2, fuel in a modified CFR engine.
Date: February 3, 1947
Creator: Imming, Harry S. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department
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Analytical determination of effect of water injection on power output of turbine-propeller engine

Description: From Introduction: "Water injection at the compressor inlet has been successfully used to increase the thrust of turbojet engines. References 1 and 2 indicate that the sea-level static thrust of a centrifugal-flow-type turbojet engine may be increased about 25 percent by use of liquid injection. Reference 3 indicates that greater thrust augmentation is possible at a compressor pressure ratio of 11 than of 4."
Date: November 3, 1949
Creator: Ross, Albert O. & Huppert, Merle C.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of cone-type diffusers designed for minimum spillage at inlet

Description: Report presenting a preliminary investigation of cone-type diffusers designed for minimum spillage at the inlet during operation in the supersonic tunnel at Mach number 1.85. Pressure recoveries of a series of stationary cones with included angles from 20 degrees to 60 degrees were investigated. Results regarding the pressure recovery with stationary cones and pressure recovery of movable-cone configurations are provided.
Date: May 3, 1948
Creator: Luidens, Roger W. & Hunczak, Henry
Partner: UNT Libraries Government Documents Department
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A flight investigation and analysis of the lateral-oscillation characteristics of an airplane

Description: Report presenting flight tests to determine the causes of undesirable dynamic lateral-stability characteristics of an airplane. Various rudder modifications were flight tested with the rudder free and fixed over an indicated airspeed range from approximately 200 to 450 miles per hour. Results regarding rudder-fixed characteristics and rudder-free characteristics are provided.
Date: June 3, 1948
Creator: Stough, Carl J. & Kauffman, William M.
Partner: UNT Libraries Government Documents Department
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Vibration of loosely mounted turbine blades during service operation of a turbojet engine with centrifugal compressor and straight-flow combustion chambers

Description: Report presenting an experimental investigation to determine the vibration characteristics of loosely mounted turbine blades during service operation of a turbojet engine. High-temperature strain gages were used to measure turbine-blade vibrations. Results regarding oscillograph records, critical speeds and frequencies, vibratory-stress levels, and effect of tightening the blade mount are provided.
Date: November 3, 1949
Creator: Morgan, W. C.; Kemp, R. H. & Manson, S. S.
Partner: UNT Libraries Government Documents Department
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Carbon deposition of 19 fuels in an annular turbojet combustor

Description: Report presenting the effects of fuel properties and change in simulated engine operating conditions on carbon deposition in an annular turbojet combustor. The fuel properties examined included specific gravity, volumetric average boiling temperature, hydrocarbon type, and hydrogen-carbon weight ratio. The fuels included hydrocarbons of the paraffinic, olefinic, and aromatic types as well as fuel mixtures.
Date: February 3, 1949
Creator: Wear, Jerrold D. & Jonash, Edmund R.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of the effects of viscosity on the drag of bodies of revolution at a Mach number 1.5

Description: Report presenting testing to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested with smooth surfaces and roughness to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. Results regarding the reduction of data, precision, effects of support interference, Schileren photographs, and theoretical calculations are provided.
Date: April 3, 1947
Creator: Chapman, Dean R. & Perkins, Edward W.
Partner: UNT Libraries Government Documents Department
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Pressure Distributions Over a Wing-Fuselage Model at Mach Numbers of 0.4 to 0.99 and at 1.2

Description: Report presenting pressure distributions over a prolate spheroid of fineness ratio 6 and over a combination of this body with an NACA 65-010 wing section for a range of Mach numbers. Results regarding wall and sting interference, nature of flow over a model in the transonic region, development of supersonic flow from subsonic flow, and a comparison of experimental and theoretical flow at subsonic stream Mach numbers are provided.
Date: November 3, 1948
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department
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Vibrational modes of several hollow turbine blades and of solid turbine blade of similar aerodynamic design

Description: Experimental study to determine the vibrational modes of several hollow turbine blades and a solid turbine blade of similar aerodynamic design. Results regarding the significance of nodal patterns, vibrational modes of six blade types, and the probability of excitation in some of the blades are provided.
Date: October 3, 1949
Creator: Kemp, R. H. & Shifman, J.
Partner: UNT Libraries Government Documents Department
open access

The effect of air-jet and strip modifications on the hydrodynamic characteristics of the streamline fuselage of a transonic airplane

Description: Report presenting 1/12-size model of a streamline fuselage modified by patterns of air jets or strips on the fuselage bottom. The effects of spacing of jets, length of jet rows, and direction of jets were determined for a simulated chine configuration. Data are presented on resistance, trim, effective hydrodynamic lift, and spray.
Date: June 3, 1949
Creator: Weinflash, Bernard; Christopher, Kenneth W. & Shuford, Charles L., Jr.
Partner: UNT Libraries Government Documents Department
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Ground Effect on Downwash Angles and Wake Location

Description: "A theoretical study was made of the reduction in downwash and the upward displacement of the wake in the presence of the ground, and some verification of theory was obtained by means of air-flow measurements made with a ground-board and image-wing combination. Methods are given for estimating the effects and numerous examples are included to illustrate the nature of these effects and to show their order of magnitude" (p. 1).
Date: October 3, 1941
Creator: Katzoff, S. & Sweberg, Harold H.
Partner: UNT Libraries Government Documents Department
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The Longitudinal Stability of Elastic Swept Wings at Supersonic Speed

Description: "The longitudinal stability characteristics of elastic swept wings of high aspect ratio experiencing bending and torsional deformations are calculated for supersonic speed by the application of linearized lifting-surface theory. A parabolic wing deflection curve is assumed and the analysis is simplified by a number of structural approximations. The method is thereby limited in application to wings of high aspect ratio for which the root effects are small" (p. 1).
Date: December 3, 1948
Creator: Frick, C. W. & Chubb, R. S.
Partner: UNT Libraries Government Documents Department
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The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

Description: "The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the true stress, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Rayleigh-Ritz method of finding upper limits" (p. 213).
Date: May 3, 1946
Creator: Budiansky, Bernard & Hu, Pai C.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Mach Number on the Aerodynamic Characteristics of a Single-Engine Pursuit Airplane as Determined From Tests of a 1/3-Scale Model

Description: Report discussing the effects of Mach number on the aerodynamic characteristics of an Allison powered single-engine pursuit airplane. Information about the lift, drag, pitching-moment characteristics, stability, tail effectiveness, and elevator effectiveness with Mach number is provided.
Date: May 3, 1945
Creator: Robinson, Robert C. & Jessen, Henry
Partner: UNT Libraries Government Documents Department
open access

Effect of fuel on performance of a single combustor of an I-16 turbojet engine at simulated altitude conditions

Description: As part of a study of the effects of fuel composition on the combustor performance of a turbojet engine, an investigation was made in a single I-16 combustor with the standard I-16 injection nozzle, supplied by the engine manufacturer, at simulated altitude conditions. The 10 fuels investigated included hydrocarbons of the paraffin olefin, naphthene, and aromatic classes having a boiling range from 113 degrees to 655 degrees F. They were hot-acid octane, diisobutylene, methylcyclohexane, benzen… more
Date: July 3, 1947
Creator: Zettle, Eugene V.; Bolz, Ray E. & Dittrich, R. T.
Partner: UNT Libraries Government Documents Department
open access

Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: "A method is described by which the total temperature of the gases at the combustion-chamber outlet of a ram-jet engine may be determined from the loss in total pressure measured across the combustion chamber. A working chart is presented by means of which the ratio of the total temperature of the gases at the combustion-chamber outlet to the total temperature of the gases at the combustion-chamber inlet may be determined from the measured loss of total pressure across the combustion chamber an… more
Date: March 3, 1947
Creator: Pinkel, I. Irving
Partner: UNT Libraries Government Documents Department
open access

Knock-Limited Blending Characteristics of Benzene, Toluene, Mixed Xylenes, and Cumene in an Air-Cooled Cylinder

Description: "An investigation was conducted to determine the knock-limited blending characteristics of leaded fuels containing selected aromatic fuel components (benzene, toluene, mixed xylenes, and cumene). Each of the aromatics was blended with an alkylate blending agent and with a virgin base stock. The blending characteristics of the resulting fuels were determined in a full-scale aircraft-engine cylinder" (p. 1).
Date: February 3, 1945
Creator: Hensley, Reece V. & Breitwieser, Roland
Partner: UNT Libraries Government Documents Department
open access

Endurance Tests of a 22-Inch-Diameter Pulse-Jet Engine With a Neoprene-Coated Valve Grid

Description: Report discussing the results of testing to determine the operating life of a 22-inch-diameter pulse-jet engine equipped with a neoprene-coated valve grid. The valve grid was found to extend the operating life and only reduced the performance slightly.
Date: October 3, 1945
Creator: Manganiello, Eugene J.; Valerino, Michael F. & Breisch, John H.
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms September 4, 1947 to September 5, 1947 at Clinton County Army Air Field, Ohio

Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 4, 1947 to September 5, 1947 are presented.
Date: April 3, 1948
Creator: Funk, Jack
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Directional Stability and Control of a P-51D Airplane with a Horn-Balanced Rudder as Compared with Previously Tested Vertical-Tail Configurations

Description: "At the request of the Air Materiel Command, Army Air Forces, flight tests were conducted on a P-5lD-20-NA (AAF No. 44-63826) airplane equipped with a horn-balanced rudder. This rudder was fitted with an unbalancing tab as was the original product fan rudder. Tests were made both with the unbalancing tab in operation and with the unbalancing tab locked. The modification to the original vertical tail consisted of removing the cap from the top of the fin and adding 1.91 square feet of area to the… more
Date: December 3, 1946
Creator: Mungall, Robert G.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning Tunnel Tests of a 1/20-Scale Model of the Chance Vought XF6U-1 Airplane, TED No. NACA 2390

Description: "A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/20-scale model of the Chance Vought XF6U-1 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the normal-fighter condition. The investigation also included tests for the take-off fighter condition (wing-tip tanks plus fuel added) spin-recovery parachutes, and simulated pilot escape" (p. 1).
Date: October 3, 1948
Creator: Klinar, Walter J.
Partner: UNT Libraries Government Documents Department
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