National Advisory Committee for Aeronautics (NACA) - 29 Matching Results

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Torsional Stiffness of Thin-Walled Shells Having Reinforcing Cores and Rectangular, Triangular, or Diamond Cross Section

Description: "A theoretical investigation has been made of the Saint-Venant torsion of certain composite bars. These bars are composed of two materials -- one material in the form of a thin-walled cylindrical shell and the other material in the form of a core which fills the interior of the shell and is bonded to it. An approximate boundary-value problem is formulated on assumptions similar to those of the theory of torsion of hollow thin-walled shells (Bredt theory)" (p. 771).
Date: June 7, 1956
Creator: McComb, Harvey G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Propagation of a free flame in a turbulent gas stream

Description: Effective flame speeds of free turbulent flames were measured by photographic, ionization-gap, and photomultiplier-tube methods, and were found to have a statistical distribution attributed to the nature of the turbulent field. The effective turbulent flame speeds for the free flame were less than those previously measured for flames stabilized on nozzle burners, Bunsen burners, and bluff bodies. The statistical spread of the effective turbulent flame speeds was markedly wider in the lean and r… more
Date: May 7, 1956
Creator: Mickelsen, William R. & Ernstein, Norman E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of elastic and plastic stress concentration factors due to notches and fillets in flat plates

Description: Six large 24s-t3 aluminum-alloy-sheet specimens containing various notches or fillets were tested in tension to determine their stress concentration factors in both the elastic and plastic ranges. The elastic stress concentration factors were found to be slightly higher than those calculated by Neuber's method and those obtained photoelastically by Frocht. The results showed further that the stress concentration factor decreases as strains at the discontinuity enter the plastic range. A general… more
Date: September 7, 1951
Creator: Hardrath, Herbert F. & Ohman, Lachlan
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Discussion of boundary-layer characteristics near the wall of an axial-flow compressor

Description: From Summary: "The boundary-layer velocity profiles in the tip region of an axial-flow compressor downstream of the guide vanes and downstream of the rotor were measured by use of total-pressure and claw-type yaw probes. These velocities were resolved into two components: one along the streamline of the flow outside the boundary layer, and the other perpendicular to it. The affinity among all profiles was thus demonstrated with the boundary-layer thickness and the deflection of the boundary lay… more
Date: June 7, 1951
Creator: Mager, Artur; Mahoney, John J. & Budinger, Ray E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of conical jet nozzles in terms of flow and velocity coefficients

Description: Performance characteristics of conical jet nozzles were determined in an investigation covering a range of pressure ratios from 1.0 to 2.8, cone half-angles from 5 degrees to 90 degrees, and outlet-inlet diameter ratios from 0.50 to 0.91. All nozzles investigated had an inlet diameter of 5 inches. The flow coefficients of the conical nozzles investigated were dependent on the cone half-angle, outlet-inlet diameter ratio, and pressure ratio. The velocity coefficients were essentially constant at… more
Date: September 7, 1948
Creator: Grey, Ralph E. & Wilsted, H. Dean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at High Speeds of the Drag of Three Airfoils and a Circular Cylinder Representing Full-Scale Propeller Shanks

Description: "Tests have been made at high speeds to determine the drag of models, simulating propeller shanks, in the form of a circular cylinder and three airfoils, the NACA 16-025, the NACA 16-040, and the NACA 16-040 with the rear 25 percent chord cut off. All the models had a maximum thickness of 4 1/2 inches to conform with average propeller-shank dimensions and a span of 20 1/4 inches. For the tests the models were supported perpendicular to the lower surface of the wing of an XP-51 airplane (p. 277). more
Date: June 7, 1946
Creator: Barlow, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank tests to determine the effect on planing-tail hulls of varying length, width, and plan-form taper of afterbody

Description: Tests were conducted in Langley Tank no. 2 on models of an unconventional flying-boat hull called a planing-tail hull to determine the effects on resistance of varying a number of afterbody parameters. The effects of varying length, width, and plan-form taper of the afterbody are presented. Tests were made with afterbodies of two widths, two lengths, and two tapers. In the tests the depth of step and the angle of afterbody keel were held constant.(author).
Date: January 7, 1946
Creator: Dawson, John R.; Walter, Robert C. & Hay, Elizabeth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the NACA 4-(5)(08)-03 and NACA 4-(10)(08)-03 two-blade propellers at forward Mach numbers to 0.725 to determine the effects of camber and compressibility on performance

Description: As part of a general investigation of propellers at high forward speeds, tests of two-blade propellers having the NACA 4-(5)(08)-03 and NACA 4-(10)(08)-03 blade designs were made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.70 to determine the effect of camber and compressibility on propeller characteristics. Results previously reported for similar tests of a two-blade propeller having the NACA 4-(3… more
Date: May 7, 1945
Creator: Delano, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Formulas for propellers in yaw and charts of the side-force derivative

Description: General formulas are given for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of the side-force derivative are given for two propellers of different plan form. The charts cover solidities of two to six blades and single and dual rotation. The blade angle ranges from 15 degrees or 20 degrees to 60 degrees.
Date: April 7, 1943
Creator: Ribner, Herbert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flutter calculations in three degrees of freedom

Description: From Summary: "The present paper is a continuation of the general study of flutter published in NACA reports nos. 496 and 685. The paper is mainly devoted to flutter in three degrees of freedom (bending, torsion, and aileron) for which a number of selected cases have been calculated and presented in graphical form. The results are analyzed and discussed with regard to the effects of structural damping, of fractional-span ailerons, and of mass-balancing. The analysis shows that more emphasis sho… more
Date: June 7, 1941
Creator: Theodorsen, Theodore & Garrick, I. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Shear lag in box beams methods of analysis and experimental investigations

Description: The bending stresses in the covers of box beams or wide-flange beams differ appreciably from the stresses predicted by the ordinary bending theory on account of shear deformation of the flanges. The problem of predicting these differences has become known as the shear-lag problem. The first part of this paper deals with methods of shear-lag analysis suitable for practical use. The second part of the paper describes strain-gage tests made by the NACA to verify the theory. Three tests published b… more
Date: March 7, 1941
Creator: Kuhn, Paul & Chiarito, Patrick T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Aging on Mechanical Properties of Aluminum-Alloy Rivets

Description: "Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24s, 17s, and a17s of the duralumin type and 53s of the magnesium-silicide type" (p. 353).
Date: February 7, 1941
Creator: Roop, Frederick C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Interrelation of Exhaust-Gas Constituents

Description: This report presents the results of an investigation conducted to determine the interrelation of the constituents of the exhaust gases of internal-combustion engines and the effect of engine performance on these relations. Six single-cylinder, liquid-cooled tests engines and one 9-cylinder radial air-cooled engine were tested. Various types of combustion chambers were used and the engines were operated at compression ratios from 5.1 to 7.0 using spark ignition and from 13.5 to 15.6 using compre… more
Date: September 7, 1937
Creator: Gerrish, Harold C. & Voss, Fred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Prechamber compression-ignition engine performance

Description: Single-cylinder compression-ignition engine tests were made to investigate the performance characteristics of prechamber type of cylinder head. Certain fundamental variables influencing engine performance -- clearance distribution, size, shape, and direction of the passage connecting the cylinder and prechamber, shape of prechamber, cylinder clearance, compression ratio, and boosting -- were independently tested. Results of motoring and of power tests, including several typical indicator cards,… more
Date: July 7, 1936
Creator: Moore, Charles S. & Collins, John H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air flow around finned cylinders

Description: Report presents the results of a study made to determine the air-flow characteristics around finned cylinders. Air-flow distribution is given for a smooth cylinder, for a finned cylinder having several fin spacings and fin widths, and for a cylinder with several types of baffle with various entrance and exit shapes. The results of these tests show: that flow characteristics around a cylinder are not so critical to changes in fin width as they are to fin spacing; that the entrance of the baffle … more
Date: November 7, 1935
Creator: Brevoort, M. J. & Rollin, Vern G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward

Description: A family of related airfoils having the position of maximum camber unusually far forward was investigated in the variable-density tunnel as an extension of the study recently completed of a large number of related airfoils. The new airfoils gave improved characteristics over those previously investigated, especially in regard to the pitching moment. Some of the new sections are markedly superior to well-known and commonly used sections and should replace them in applications requiring a slightl… more
Date: May 7, 1935
Creator: Jacobs, Eastman N. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Lateral Control Devices for Use With Full-Span Flaps

Description: This report presents the results of flight tests made on five different lateral control devices that appeared adaptable to wings fitted with full span flaps: controllable auxiliary airfoils (airfoils mounted above and forward of the leading edge of the wings), external ailerons (airfoils mounted above the wing and slightly forward of its maximum ordinate), upper-surface ailerons (similar to split trailing-edge flaps except that they constitute the upper surface of the wing), ailerons that retra… more
Date: November 7, 1934
Creator: Soulé, H. A. & McAvoy, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of nacelle-propeller combinations in various positions with reference to wings 6: wings and nacelles with pusher propeller

Description: This report is the sixth of a series giving wind tunnel tests results on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. The present report gives the results of tests of a radial-engine nacelle with pusher propeller in 17 positions with reference to a Clark Y wing; tests of the same nacelle and propeller in three positions with reference to a thick wing; and tests of a body and pusher propeller with the thick wing, simulating the case of a propeller drive… more
Date: June 7, 1934
Creator: Wood, Donald H. & Bioletti, Carlton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Forces and Moments Exerted on a Spinning Model of the NY-1 Airplane as Measured by the Spinning Balance

Description: From Summary: "A preliminary investigation of the effects of changes in the elevator and rudder settings and of small changes in attitude upon the aerodynamic forces and moments exerted upon a spinning airplane was undertaken with the spinning balance in the 5-foot vertical tunnel of the National Advisory Committee for Aeronautics. The tests were made on a 1/12-scale model of the "NY-1" airplane. Data by which to fix the attitude, the radius of spin, and the rotational and air velocities were t… more
Date: February 7, 1933
Creator: Bamber, M. J. & Zimmerman, C. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drop and Flight Tests on NY-2 Landing Gears Including Measurements of Vertical Velocities at Landing

Description: This investigation was conducted to obtain quantitative information on the effectiveness of three landing gears for the NY-2 (consolidated training) airplane. The investigation consisted of static, drop, and flight tests on landing gears of the oleo-rubber-disk and the mercury rubber-chord types, and flight tests only on a landing gear of the conventional split-axle rubber-cord type. The results show that the oleo gear is the most effective of the three landing gears in minimizing impact forces… more
Date: August 7, 1931
Creator: Peck, W. C. & Beard, A. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method of flight measurement of spins

Description: A method is described involving the use of recording turn meters and accelerometers and a sensitive altimeter, by means of which all of the physical quantities necessary for the complete determination of the flight path, motion, attitude, forces, and couples of a fully developed spin can be obtained in flight. Data are given for several spins of two training type airplanes which indicate that the accuracy of the results obtained with the method is satisfactory.
Date: October 7, 1930
Creator: Soulé, Hartley A. & Scudder, Nathan F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Temperature coefficient of the modulus of rigidity of aircraft instrument diaphragm and spring materials

Description: Experimental data are presented on the variation of the modulus of rigidity in the temperature range -20 to +50 degrees C. of a number of metals which are of possible use for elastic elements for aircraft and other instruments. The methods of the torsional pendulum was used to determine the modulus of rigidity and its temperature coefficient for aluminum, duralumin, monel metal, brass, phosphor bronze, coin silver, nickel silver, three high carbon steels, and three alloy steels. It was observed… more
Date: March 7, 1930
Creator: Brombacher, W. G. & Melton, E. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of variation of chord and span of ailerons on rolling and yawing moments at several angles of pitch

Description: This report presents the results of an extension to higher angles of attack of the investigation of the rolling and yawing moments due to ailerons of various chords and spans on two airfoils having the Clark Y and U. S. A. 27 wings. The measurements were made at various angles of pitch but at zero angle of roll and yaw, the wing chord being set at an angle of +4 degrees to the fuselage axis. In the case of the Clark Y airfoil the measurements have been extended to a pitch angle of 40 degrees, u… more
Date: October 7, 1929
Creator: Heald, R. H.; Strother, D. H. & Monish, B. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure element of constant logarithmic stiffness for temperature compensated altimeter

Description: From Summary: "The usual type of altimeter contains a pressure element, the deflections of which are approximately proportional to pressure changes. An evenly divided altitude scale is secured by using a mechanism between the pressure element and pointer which gives the required motion of the pointer. A temperature-compensated altimeter was constructed at the Bureau of Standards for the Bureau of Aeronautics of the Navy Department which contained a manually operated device for controlling the m… more
Date: August 7, 1928
Creator: Brombacher, W. G. & Cordero, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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