National Advisory Committee for Aeronautics (NACA) - 334 Matching Results

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A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blend

Description: "The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends" (p. 1).
Date: 1943
Creator: Sanders, Newell D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Operating Temperatures of a Sodium-Cooled Exhaust Valve as Measured by a Thermocouple

Description: Report presents the results of a thermocouple installed in the crown of a sodium-cooled exhaust valve. The valve was tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 degrees F. was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 r.p.m.
Date: 1943
Creator: Sanders, J. C.; Wilsted, H. D. & Mulcahy, B. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A preliminary study of the effect of compressive load on the fairness of a low-drag wing specimen with Z-section stiffeners

Description: "A low-drag airfoil specimen was loaded in compression, and surveys of the fairness of the surface were made at different stresses as well as at zero load after successively higher stresses had been applied and removed. The tests reported and the discussion of the significance of the results obtained suggest a procedure for determining the probable outcome of a particular type of construction for a low-drag wing" (p. 1).
Date: January 1943
Creator: Jacobs, Eastman N.; Lundquist, Eugene E.; Davidson, Milton & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Distribution in Nonuniform Two-Dimensional Flow

Description: In an attempt to follow the time rate of change of the processes in turbulent flows by quantitative measurements the measurement of the pressure is often beset with insuperable difficulties for the reason that the speeds and hence the pressures to be measured are often very small. On the other hand, the measurement of very small pressures requires, at least, considerable time, so that the follow-up of periodically varying processes is as goad as impossible. In order to obviate these difficultie… more
Date: January 1943
Creator: Schwabe, M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The problem of longitudinal stability and control at high speeds

Description: In high-speed dives many airplanes exhibit a dangerous tendency to continue diving in spite of the application of large control forces. Wind-tunnel tests have confirmed that these difficulties are not peculiar to any particular configuration, so that the problem is of interest to all designers of high-speed airplanes. The purpose of this report is to acquaint designers with the cause of difficulties and with the means now known for their alleviation.
Date: 1943
Creator: Hood, Manley J. & Allen, H. Julian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The significance of the time concept in engine detonation

Description: Report presenting an experimental technique developed by means of which the variables affecting the time element in the detonation process in a spark-ignition engine can be controlled and approximately measured. Results indicated that higher maximum permissible pressures can be used if the rate of compression of the end gas is increased. Suggestions for future study are provided.
Date: January 1943
Creator: Leary, W. A. & Taylor, E. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and Control Tests of a 3/4-Scale Model of the XP-69 Airplane in the NACA Full-Scale Tunnel

Description: Report presenting tests in the full-scale tunnel to determine the longitudinal- and lateral-stability and control characteristics of a scale model of the XP-69 airplane. The data include measurements of the forces and moments on the model at various angles of attack and angles of yaw. The effects of elevator, rudder, and aileron deflection on control-surface effectiveness and on hinge moments were determined.
Date: January 1943
Creator: Sweberg, Harold H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Airfoils Designed to Delay the Compressibility Burble

Description: "Fundamental investigations of compressibility phenomena for airfoils have shown that serious adverse changes of aerodynamic characteristics occur as the local speed over the surface exceeds the local speed of sound. These adverse changes have been delayed to higher free-stream speeds by development of suitable airfoil shapes. The method of deriving such airfoil shapes is described, and aerodynamic data for a wide range of Mach numbers obtained from tests of these airfoils in the Langley 24-inc… more
Date: 1943
Creator: Stack, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Aluminum-Alloy Stiffened-Sheet Specimens Cut From an Airplane Wing

Description: "The specimens used in the present tests were cut from an actual airplane wing of the stressed-skin type. The specimens thus obtained were not representative of the usual type of laboratory specimens because the stiffeners were not exactly parallel nor evenly spaced and, in one case, the skin consisted of pieces of sheet of different thicknesses. The test data obtained indicate that the buckling strain of stiffened curved sheet can be computed with reasonable accuracy by the equation given by W… more
Date: January 1943
Creator: Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of flat panels with four types of stiffeners

Description: Report presenting testing of fifty-one aluminum-alloy panels as flat-end columns. The test specimens included all possible combinations of two lengths, four stiffener spacings, and four stiffener designs, and were mostly in duplicate pairs. Results regarding the panel bending tests, panel compression tests, and column tests of individual stiffeners are provided.
Date: January 1943
Creator: Niles, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of two models representing intermediate inboard and outboard wing sections of the XB-36 airplane

Description: Report presenting testing in the two-dimensional low-turbulence pressure tunnel and the two-dimensional low-turbulence tunnel of two models made by the Consolidated Aircraft Corporation, one of the outboard section and one of the inboard section.
Date: January 1943
Creator: Bogdonoff, Seymour M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory and preliminary flight tests of an all-movable vertical tail surface

Description: Report presenting flight testing of an improved type of all-movable tail surface. The particular arrangement tested provides control-free stability and a stable variation of the control forces during maneuvers. Results regarding rudder effectiveness, directional stability, rudder-free lateral motion, and rudder-free turns are provided.
Date: January 1943
Creator: Jones, Robert T. & Kleckner, Harold F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Torsion tests of 24S-T aluminum-alloy noncircular bar and tubing

Description: From Summary: "Tests of 24S-T aluminum alloy have been made to determine the yield and ultimate strengths in torsion of noncircular bar and tubing. An approximate basis for predicting these torsional strength characteristics has been indicated. The results show that the torsional stiffness and maximum shearing stresses within the elastic range may be computed quite closely by means of existing formulas based on mathematical analysis and the membrane analogy."
Date: January 1943
Creator: Moore, R. L. & Paul, D. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Torsional Elastic Properties of 18:8 Chromium-Nickel Steel as Affected by Plastic Deformation and by Heat Treatment

Description: Note presenting a study made of the relationship between torsional stress, strain, and permanent set for 18:8 chromium-nickel steel in the annealed, half-hard, and hard conditions. The influence of plastic extension, plastic torsion, and annealing temperature on the torsional elastic properties is discussed.
Date: January 1943
Creator: Mebs, R. W. & McAdam, D. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Torsional strength of aluminum-alloy round tubing

Description: Report presenting an analysis of existing data on aluminum-alloy tubing with a wide range of plastic properties in order to establish a useful empirical relationship between tensile yield and ultimate strengths, diameter-thickness ratios, and torsional strengths within the range of plastic buckling.
Date: January 1943
Creator: Moore, R. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing

Description: Report presenting an investigation in the 7- by 10-foot tunnel of various modifications of the trailing-edge portion of a 0.20-chord plain aileron on a partial-span model of a tapered low-drag wing. The modifications tested included various amounts of symmetrical and unsymmetrical thickening and beveling of the aileron trailing edge. Results regarding coefficients and corrections, characteristics with ailerons neutral, characteristics with ailerons deflected, aileron trim characteristics, and e… more
Date: January 1943
Creator: Purser, Paul E. & McKee, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Plain Aileron with Various Trailing-Edge Modifications on a Tapered Wing 3: Ailerons with Simple and Spring-Linked Balancing Tabs

Description: Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controlllability at low speeds.
Date: January 1943
Creator: Purser, Paul E. & Rogallo, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Investigation of Control-Surface Characteristics 11: Various Large Overhang and Internal-Type Aerodynamic Balances for a Straight- Contour Flap on the NACA 0015 Airfoil

Description: Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the characteristics of several different shaped overhang-type aerodynamic balances applied to a straight-contour flap mounted on an NACA 0015 airfoil. The flap with blunt-nose overhang was overbalanced throughout certain ranges of flap deflection. Results regarding precision, lift, flap hinge moments, pitching moment, and drag are provided.
Date: January 1943
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Investigation of Control Surface Characteristics: [Part] 12 - Various Cover-Plate Alinements on the NACA 0015 Airfoil With a 30 Percent Chord Flap and Large Sealed Internal Balance

Description: Report presenting force-test measurements in two-dimensional flow made in the 4- by 6-foot vertical tunnel to determine the aerodynamic effects of changing the alignment of the cover plates on a sealed internally balanced flap. Manufacturing imperfections in the alignment of the cover plates with the airfoil contour may have serious effects on the resultant hinge moment of a flap with a sealed internal balance. Results regarding lift, flap hinge moments, pitching moment, and drag are provided.
Date: January 1943
Creator: Hoggard, H. Page, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Description: Report presenting the results of flight investigations showing that a beveled trailing-edge aileron gives as low or a lower profile drag than a contour aileron. Section profile drag and lift coefficients with two different types of ailerons were obtained at 3 different Reynolds numbers.
Date: January 1943
Creator: Abbott, Frank T., Jr. & Underwood, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a Twin-Engine Model to Determine the Effect of Direction of Propeller Rotation on the Static-Stability Characteristics

Description: Report presenting tests made in the 7- by 10-foot tunnel to determine the effect of direction of propeller rotation on the static longitudinal and lateral stability characteristics of the scale model of the North American B-28 airplanes. The results of the present investigation indicate that the mode of propeller operation has a considerable effect upon lateral and longitudinal stability and may have an effect upon propulsive efficiency.
Date: January 1943
Creator: Rogallo, Francis M. & Swanson, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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