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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
open access

A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls

Description: "The gross weight, beam, and afterbody length of 12 contemporary flying boats and amphibians with pointed afterbodies are tabulated and correlated. For most of the hulls considered, the afterbody length-beam ratios are shown to be directly proportion to the gross-load coefficients" (p. 1).
Date: June 1946
Creator: Parkinson, John B.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Effect of Rotor-Tip Speed on Helicopter Hovering Performance and Maximum Forward Speed

Description: Report presenting a study of several sample helicopters in order to evaluate the effect of rotor-tip speed on hovering performance and limiting forward speed. The main purpose of the study was to determine whether hovering performance could be increased by the use of lower tip speeds without undue sacrifice in maximum forward speed. Results regarding typical helicopters, low-solidity helicopters, and high-speed helicopters are provided.
Date: March 1946
Creator: Gustafson, F. B. & Gessow, Alfred
Partner: UNT Libraries Government Documents Department
open access

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudde… more
Date: March 1946
Creator: Kayten, Gerald G. & Koven, William
Partner: UNT Libraries Government Documents Department
open access

Experimental Determination of the Effect of Negative Dihedral on Lateral Stability and Control Characteristics at High Lift Coefficients

Description: Report presenting the effects of negative dihedral on lateral stability and control characteristics at high lift coefficients determined by flight tests with a model. As the effective dihedral was decreased, the model became increasingly difficult to fly. Results regarding the effect of directional stability and lift coefficient on flight behavior are also provided.
Date: January 1946
Creator: McKinney, Marion O., Jr.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Lateral Area on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Langley Free-Flight Tunnel

Description: Report presenting the effects of large variations of lateral area on the lateral stability and control characteristics of a free-flying model when ailerons are used as the principal control as determined by flight tests. The effects of the lateral-force parameter were investigated for a wide range of values of the directional-stability parameter and the rotary-damping-in-yaw parameter.
Date: February 1946
Creator: Drake, Hubert M.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics of Plain and Balanced Flaps on an NACA 0009 Elliptical Semispan Wing

Description: Report discusses a series of force tests of a NACA 0009 elliptical semispan wing equipped with a flap that is either 50 percent of the wing area or 30 percent of the wing area. Information about the lift, hinge moment, and drag and pitching moment is provided.
Date: February 1946
Creator: Tamburello, Vito; Smith, Bernard J. & Silvers, H. Norman
Partner: UNT Libraries Government Documents Department
open access

Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane

Description: An analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver… more
Date: March 1946
Creator: Pearson, Henry A. & Aiken, William S., Jr.
Partner: UNT Libraries Government Documents Department
open access

An analysis of the skipping characteristics of some full-size flying boats

Description: From Introduction: "The purpose of this report is to gather together in one place information on the skipping characteristics of number of flying boats. A graph showing the influence of the hull form on the skipping characteristics is given which should be useful in laying out the proportions of the hull in preliminary design to insure good landing behavior."
Date: January 1946
Creator: Locke, F. W. S., Jr.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements to Determine Effect of a Spring-Loaded Tab on Longitudinal Stability of an Airplane

Description: "In conjunction with a program of research on the general problem of stability of airplanes in the climbing condition, tests have been made of a spring-loaded tab, which is referred to as a "springy tab," installed on the elevator of a low-wing scout bomber. The tab was arranged to deflect upward with decrease in speed which caused an increase in the pull force required to trim at low speeds and thereby increased the stick-free static longitudinal stability of the airplane. It was found that th… more
Date: February 1946
Creator: Hunter, Paul A. & Reeder, John P.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Tail and Wing-Tip Spin-Recovery Parachutes as Determined by Tests in the Langley 20-Foot Free-Spinning Tunnel

Description: Report presenting tests of spin-recovery parachutes on six models of typical fighter and trainer airplanes conducted in the 20-foot free-spinning tunnel to obtain data for correlating model and full-scale results. Parachutes attached to the tail of the models, to the outer wing tip, to the inner wing tip, and to both wing tips were tested. Results regarding parachute construction, loading variations, effect of test altitude, and action of spin-recovery parachutes are provided.
Date: March 1946
Creator: Kamm, Robert W. & Malvestuto, Frank S., Jr.
Partner: UNT Libraries Government Documents Department
open access

JRM-1 Landing Impact Characteristics From Model Tests

Description: Report presenting a series of dynamic tests undertaken on a model of a hull of JRM-1 in order to provide information on the probable water loads during rough water landings. The impact acceleration and trim data are analyzed to show the trend of accelerations with wave size and length-height ratio.
Date: February 1946
Creator: Pierson, J. D.
Partner: UNT Libraries Government Documents Department
open access

Spray Characteristics of a Powered Dynamic Model of a Flying Boat Having a Hull With a Length-Beam Ratio of 9.0

Description: Report discusses an investigation into the spray characteristics of a twin-engine flying boat model similar to the Boeing XPBB-1 but with a modified length-beam ratio of the hull. The spray characteristics of the modified model compared favorably with the standard XPBB-1 flying boat and no adverse effects on spray characteristics were introduced by modifying the length-beam ratio and hull.
Date: January 1946
Creator: Olson, Roland E. & Bell, Joe W.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 14S-T Aluminum Alloy

Description: "Column and plate compressive strengths of extruded 14S-T aluminum alloy were determined both within and beyond the elastic range from tests of flat-end H-section columns and from local-instability tests of H-, Z-, and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircra… more
Date: May 1946
Creator: Heimerl, George J. & Niles, Donald E.
Partner: UNT Libraries Government Documents Department
open access

Charts for Critical Combinations of Longitudinal and Transverse Direct Stress for Flat Rectangular Plates

Description: Report presenting the use of the energy method to derive interaction equations that define the critical combinations of longitudinal and transverse direct stress for isotropic flat rectangular plates with four different edge conditions. Charts based on the interaction equations are presented for the four cases.
Date: March 1946
Creator: Libove, Charles & Stein, Manuel
Partner: UNT Libraries Government Documents Department
open access

Progress Report on Strength and Creep of Special Ceramic Bodies in Tension at Elevated Temperatures

Description: Report presenting an investigation for the determination of the behavior of ceramic bodies in tension at elevated temperatures for the purpose of determining data for the design of ceramic blades for gas turbines. Observations were made of six special ceramic bodies in order to determine their tensile strength and creep during prolonged loading under a range of stresses and temperatures.
Date: June 1946
Creator: Geller, R. F. & Burdick, M. D.
Partner: UNT Libraries Government Documents Department
open access

Knock-Limited Performance of N-Methylaniline and Xylidine Blends in an Air-Cooled Aircraft Cylinder

Description: Report presenting an investigation of the antiknock effectiveness of N-methyl-aniline and xylidines as fuel additives under severe engine operating conditions. 5-percent concentrations by weight were blended with an alkylate blending agent and a virgin-base gasoline.
Date: February 1946
Creator: Bull, Arthur W.; Stricker, Edward G. & Wear, Jerrold D.
Partner: UNT Libraries Government Documents Department
open access

Knock-limited performance tests of 2, 2, 3, 4-tetramethylpentane, 2, 3, 3, 4-tetramethylpentane, 3, 4, 4-trimethyl-2-pentane, and 2, 3, 4-trimethyl-2-pentane in small-scale and full-scale cylinders

Description: Report presenting knock-limited tests using F-4, F-3, and 17.6 small-scale engines and a full-scale cylinder on blends containing four different types of hydrocarbons. Each of the hydrocarbons was individually blended in various concentrations with three base fuels.
Date: March 1946
Creator: Jonash, Edmund R.; Meyer, Carl L. & Branstetter, J. Robert
Partner: UNT Libraries Government Documents Department
open access

A Correlation of the Effects of Compression Ratio and Inlet-Air Temperature on the Knock Limits of Aviation Fuels in a CFR Engine 2

Description: Report presenting the knock-limited performance of nine fuels comprising isolated members of four classes of hydrocarbons in the form of three-dimensional plots of fuel-air ratio, compression temperature, and compression-air density.
Date: June 1946
Creator: Alquist, Henry E.; O'Dell, Leon & Evvard, John C.
Partner: UNT Libraries Government Documents Department
open access

Knock-limited performance of pure hydrocarbons blended with a base fuel in a full-scale aircraft-engine cylinder 3: four aromatics, six ethers

Description: Report presenting knock-limited performance tests of leaded blends of four pure aromatic hydrocarbons and six pure ethers with a base fuel in a full-scale aircraft-engine cylinder at two operating conditions to determine the antiknock effectiveness of additions of pure compounds to aviation fuels.
Date: March 1946
Creator: Jones, Arthur W.; Bull, Arthur W. & Jonash, Edmund R.
Partner: UNT Libraries Government Documents Department
open access

Determination of Towline Tension and Stability of Spin-Recovery Parachutes

Description: Report presenting testing of a number of spin-recovery parachutes varying in size in order to determine the force exerted by the parachutes on the towline and the stability of the parachutes. The effects of modifications to the parachutes regarding towline tension and stability are also provided. Results regarding the parachute motions, air forces on parachutes, shock loads, and effects of modifications to line length and canopy vent are provided.
Date: March 1946
Creator: Wood, John H.
Partner: UNT Libraries Government Documents Department
open access

Critical Combinations of Longitudinal and Transverse Direct Stress for an Infinitely Long Flat Plate With Edges Elastically Restrained Against Rotation

Description: Report presenting a theoretical investigation of the buckling of an infinitely long flat plate with edges elastically restrained against rotation under combinations of longitudinal and transverse direct stress. Interaction curves are presented that give the critical combinations of stress for several different degrees of elastic edge restraint, including simple support and complete fixity.
Date: March 1946
Creator: Batdorf, S. B.; Stein, Manuel & Libove, Charles
Partner: UNT Libraries Government Documents Department
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