Technical Report Archive & Image Library (TRAIL) - 185 Matching Results

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Maneuverability investigation of an F6C-4 fighting airplane: "In order to compare the relative maneuverability of two fighting airplanes and to accumulate additional data to assist in establishing a satisfactory criterion for the maneuverability of any airplane, the National Advisory Committee for Aeronautics has conducted maneuverability investigations on the F6C-3 (water-cooled engine) and the F6C-4 (air-cooled engine) airplanes. The investigation made on the F6C-3 airplane was reported in NACA-TR-369. This report contains the results of the investigation made on the F6C-4 airplane" (p. 475).
A balanced diaphragm type of maximum cylinder pressure indicator: A balanced diaphragm type of maximum cylinder pressure indicator was designed to give results consistent with engine operating conditions. The apparatus consists of a pressure element, a source of controlled high pressure and a neon lamp circuit. The pressure element, which is very compact, permits location of the diaphragm within 1/8 inch of the combustion chamber walls without water cooling. The neon lamp circuit used for indicating contact between the diaphragm and support facilitates the use of the apparatus with multicylinder engines.
English Airplane Construction: English airplane construction is presented with a particular emphasis on metal construction techniques. Steel rib and fuselage construction are discussed as well as the use of duralumin in construction.
Experiments with a model water tunnel: This report describes a model water tunnel built in 1928 by the NACA to investigate the possibility of using water tunnels for aerodynamic investigations at large scales. The model tunnel is similar to an open-throat wind tunnel, but uses water for the working fluid.
The Fiat "TR.1" Training and Touring Airplane (Italian): A Two-Place High-Wing Monoplane: Circular presenting a description of the Fiat T.R.1 airplane, which has been created for training and long-distance touring. Information regarding the fuel tanks, aircraft design, controls, tail characteristics, and flight characteristics is provided.
The Handley Page Type 42 Commercial Airplane (British): A Metal Sesquiplane: Circular presenting a description of the Handley Page 42, which is an all-metal sesquiplane. Details are provided of the cockpit, wings, fuselage, tail, power plant, landing gear, controls, and flying qualities.
Riveting in Metal Airplane Construction Part 1 : Riveting Methods and Equipment in German Metal Airplane Construction: "Although all constructors in Germany use duralumin quite frequently, and prefer cold riveting exclusively for permanent (nondetachable) connections of individual structural components, their methods and equipment are very diversified. The differences are due to a great extent to the diversity of structural types and to the special shapes of the individual subassemblies. The results is that different manufacturers have developed totally different riveting methods, as well as entirely different working methods" (p. 1).
Riveting in Metal Airplane Construction Part 2: Riveting Methods and Equipment (Concluded), Strength of Riveted Joints in Duralumin: This report includes descriptive material on rivet inspection, types of rivets and sizes. Tabular data on shearing strength of rivets at failure, ultimate shear of various rivets, tensile tests of rivet plate, and tensile strength values of riveted joints are provided.
Riveting in Metal Airplane Construction Part 3: Strength of Riveted Joints in Duralumin (Continued), Test Installation and Arrangement: This report includes strength of riveted joints in duralumin, descriptions of test procedure and results of tests. Tabulated data includes: curshing strength by failure for various conditions, shearing strength of hole edge zone in direction of tearing, tearing strengths of plates weakened by rivet holes, and enlargement of holes at beginning of break.
Riveting in Metal Airplane Construction Part 4: Strength of Riveted Joints in Duralumin (Concluded), Comparative Tests With Riveted Joints: Tests were made to determine the crushing strength of a riveted joint, in order to define the difference in crushing stregth between a strictly bolted joint and a riveted joint. The object was to tabulate the crushing strength by failure on various plate thicknesses for a one-rivet double-shear riveted joint.
Full-scale tests of metal propellers at high tip speeds: This report describes tests of 10 full-scale metal propellers of several thickness ratios at various tip speeds up to 1,350 feet per second. The results indicate no loss of efficiency up to tip speeds of approximately 1,000 feet per second. Above this tip speed the loss is at a rate of about 10 per cent per 100 feet per second increase relative to the efficiency at the lower speeds for propellers of pitch diameter ratios 0.3 to 0.4. Propellers having sections of small thickness ratio can be run at slightly higher speeds than thick ones before beginning to lose efficiency.
Accelerated Laboratory Test for Determination of Slacking Characteristics of Coal: Report issued by the U.S. Bureau of Mines on laboratory testing developed to measure the slacking of coals. Testing methods and results are presented. This report includes tables and graphs.
Bending Tests of Metal Monocoque Fuselage Construction: Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Effect of the Angular Position of the Section of a Ring Cowling on the High Speed of an XF7C-1 Airplane: The tests herein reported were conducted by the NACA to determine the effect of the angular position of the section of a ring cowling on the speed of an airplane having a radial air-cooled engine.
An investigation of the phenomenon of separation in the air flow around simple quadric cylinders: The tests, conducted at the Guggenheim Aeronautical Laboratory of Stanford University, to investigate the phenomenon of separation in the air flow past geometric shapes are described in this report.
Mathematical treatise on the recovery from a flat spin: In this mathematical investigation, made in collaboration with Dr. Wilhelm Schmidt, we interpret the temporary change (due to some disturbance) in the quantities which define the position of the airplane while in a flat spin. We further examine the effect of this change, of the means resorted to to produce the disturbance, and thus reveal the expedients available for recovering from a flat spin.
Metal Covering of Airplanes: This paper presents a relative determination of the wrinkling of a plate wall beam with variable number of supports and methods of attachment. The discussion is based entirely on tests with extensometer readings and number of wrinkles, with complete web and with cutout sections. The author notes that the number of corrugations increase with added stress, keeping constant edge spacing.
Practical Tests With The "Auto Control Slot" Part 1: Lecture: "The effect of a slotted wing depends essentially on the fact that a secondary flow branches off from the main flow and passes to the suction side of the profile. It is thus possible to delay the separation greatly and increase the lift. The practical aspect of the slotted wing is less known in Germany, especially the results obtained during the last three years since the introduction of the 'auto control slot'" (p. 1).
Practical Tests With The "Auto Control Slot" Part 2: Discussion: "For some time the D.V.L. has been investigating the question of applicability of Handley Page slotted wings to German airplanes. Comparitive gliding tests were made with open and closed slots on an Albatros L 75 airplane equipped with the Handley Page "auto control slots." This investigation served to determine the effect of the auto control slot on the properties and performances of airplanes at large angles of attack. The most important problems were whether the angle of glide at small angles of attack can be increased by the adoption of the auto control slot and, in particular, as to whether the flight characteristics at large angles of attack are improved thereby and equilibrium in gliding flight is guaranteed even at larger than ordinary angles of attack" (p. 1).
Riveted Joints in Thin Plates: The method of riveting by forming the closing head under increasing pressure or by a series of hammer blows is investigated. The question as to the best edge distance, i.e. that distance from the rivet center to the plate edge below which it is unadvisable to go and, at the same time useless to go beyond, was examined. The slippage of plates which occurs under the effect of a certain stress, does not completely disappear on unloading.
Some Characteristics of Fuel Sprays From Open Nozzles: "The penetration and cone-angle of fuel sprays from open nozzles were recorded with the NACA Spray Photography Equipment. The results show that for injection systems in which the rate of pressure rise at the discharge orifice is high, open nozzles give spray-tip velocities and penetrations which compare favorably with those of closed nozzles. The spray cone-angle was the same for all tests, although open nozzles having different orifice diameters were used, and one nozzle was used both as an open and as a closed nozzle" (p. 1).
Vickers "Viastra I" Commercial Airplane (British): A High-Wing All-Metal Semicantilever Monoplane: Circular describing the Vickers Viastra I, which is a commercial high-wing all-metal semicantilever monoplane. Details of the structure, fuselage, wings, fuel tanks, landing gear, tail, cabin, cockpit, characteristics, drawings, and photographs are provided.
Elastic Instability of Members Having Sections Common in Aircraft Construction: "Two fundamental problems of elastic stability are discussed in this report. In part one formulas are given for calculating the critical stress at which a thin, outstanding flange of a compression member will either wrinkle into several waves or form into a single half wave and twist the member about its longitudinal axis. In part two the lateral buckling of beams is discussed" (p. 373).
Present Status of Aircraft Instruments: This report gives a brief description of the present state of development and of the performance characteristics of instruments included in the following group: speed instruments, altitude instruments, navigation instruments, power-plant instruments, oxygen instruments, instruments for aerial photography, fog-flying instruments, general problems, summary of instrument and research problems. The items considered under performance include sensitivity, scale errors, effects of temperature and pressure, effects of acceleration and vibration, time lag, damping, leaks, elastic defects, and friction.
Comparison of full-scale propellers having R.A.F.-6 and Clark Y airfoil sections: In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the propellers with R. A. F.-6 sections gave about the same maximum efficiency as the Clark Y propellers and were more efficient for the conditions of climb and take-off.
Static, Drop, and Flight Tests on Musselman Type Airwheels: The purpose of this investigation was to obtain quantitative information on the shock-reducing and energy-dissipating qualities of a set of 30 by 13-6 Musselman type airwheels. The investigation consisted of static, drop, and flight tests. The static tests were made with inflation pressures of approximately 0, 5, 10, 15, 20, and 25 pounds per square inch and loadings up to 9,600 pounds.
A method of flight measurement of spins: 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.
An Accurate Method of Measuring the Moments of Inertia of Airplanes: From Summary: "This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent."
Analytical Determination of the Load on a Trailing Edge Flap: From Summary: "This report presents a theoretical analysis of the lift on a trailing edge flap. An analytical expression has been derived which enables the computation of the flap load coefficient. The theoretical results seem to show a fair agreement with the meager experimental results which are available."
The Behm Acoustic Sounder for Airplanes With Reference to Its Accuracy: Relative altimetry is of great importance for increasing the safety in aerial transportation, because it makes possible safe flying at night, by poor visibility, and when landing. Among the instruments of this type is the Behm sounder, which operates on an acoustic principle. Acoustic altimetry in general and the Behn sounder, in particular, are covered in this report.
Counter-Propeller: A counter-propeller is a fixed propeller smaller than the main propeller, mounted either fore or aft of the latter and performing the function of changing the direction of motion of the fluid filaments, which naturally tend to adopt a helicoidal form. This paper presents a consideration of the real advantage of counter-propellers on aircraft and the best shape of the blades. First, the author determines the possible energy absorption by the tangential increments. This process will be facilitated by the examination of the polygons of the relative velocities fore and aft of the generic section, of radius r, of one of the blades of the propeller.
Diesel-Engine Investigations: Ignition-Chamber Engines: This report presents a thorough investigation of the functioning process and injection and combustion characteristics of ignition-chamber engines.
Effect of Orifice Length-Diameter Ratio on Spray Characteristics: "The effect of variations of orifice length to diameter ratio on spray characteristics was determined for a 0.014-inch and a 0.040-inch orifice for ratio of 0.5 to 4.0. The nozzles containing the orifices were mounted in an injection valve and tested with a plan stem and with a helically grooved stem. The injection pressure was varied from 4000 to 8000 pounds per square inch. The air density into which the fuel was sprayed was varied from the density obtained with a pressure of 60 pounds per square inch to the density obtained with a pressure of 250 pounds per square inch at room temperature" (p. 1).
Göttingen Six-Component Scale Measurements on a Junkers A 35 Airplane Model: The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes.
Methods for the Identification of Aircraft Tubing of Plain Carbon Steel and Chromium-Molybdenum Steel: The survey of the possibilities for distinguishing between plain carbon and chromium-molybdenum steel tubing included the Herbert pendulum hardness, magnetic, sparks, and chemical tests. The Herbert pendulum test has the disadvantages of all hardness tests in being limited to factory use and being applicable only to scale-free, normalized material. The small difference in the range of hardness values between plain carbon and chromium-molybdenum steels is likewise a disadvantage.
Velocity Distribution in the Boundary Layer of a Submerged Plate: This report deals with the measurement of the velocity distribution of the air in the velocity of a plate placed parallel to the air flow. The measurements took place in a small wind tunnel where the diameter of the entrance cone is 30 cm and the length of the free jet between the entrance and exit cones is about 2.5 m. The measurements were made in the free jet where the static pressure was constant, which was essential for the method of measurement used.
Westland "Wessex" Commercial Airplane (British): A High-Wing Semicantilever Monoplane: Circular presenting a description of the Westland Wessex, which differs from other airplanes of its class because of the mounting of the outboard engines on outriggers from the fuselage and the placing of the engines in such a way that the slipstream does not interfere with the movement of the wing. A description of the design, flight characteristics, blueprints, and photographs are provided.
Some approximate equations for the standard atmosphere: This report contains the derivation of a series of simple approximate equations for density ratios and for the pressure ratio in the standard atmosphere. The accuracy of the various equations is discussed and the limits of applications are given. Several of these equations are in excellent agreement with the standard values.
Coefficients of discharge of fuel-injection nozzles for compression-ignition engines: "This report presents the results of an investigation to determine the coefficients of discharge of nozzles with small, round orifices of the size used with high-speed compression-ignition engines. The injection pressures and chamber back pressures employed were comparable to those existing in compression-ignition engines during injection. The construction of the nozzles was varied to determine the effect of the nozzle design on the coefficient. Tests were also made with nozzles assembled in an automatic injection valve, both with a plain and with a helically grooved stem" (p. 193).
Alterations and Tests of The "Farnboro" Engine Indicator: "The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of putting pressure lines on the record" (p. 1).
The Breguet 270 General-Purpose Military Airplane (French): A Two-Seat All-Steel Sesquiplane: Circular presenting a description of the Breguet 270 general-purpose military airplane, which is a two-set, all-steel sesquiplane. Details regarding the basic principles of design, construction, components, flying qualities, drawings, and photographs are provided.
Determination of the Maximum Control Forces and Attainable Quickness in the Operation of Airplane Controls: "This report is intended to furnish bases for load assumptions in the designing of airplane controls. The maximum control forces and quickness of operation are determined. The maximum forces for a strong pilot with normal arrangement of the controls is taken as 1.25 times the mean value obtained from tests with twelve persons. Tests with a number of persons were expected to show the maximum forces that a man of average strength can exert on the control stick in operating the elevator and ailerons and also on the rudder bar" (p. 1).
Effects of the End Fixation of Airplane Struts: The main purpose of this report is to give references to literature on the subject of end fixation of airplane struts and also to furnish the constructor with a general survey of the simplest methods for estimating the end-fixation effect.
Flight Tests for the Determination of Static Longitudinal Stability: The accuracy of the instruments used for flight test measurements has been inadequate so a new series of tests were commissioned with the development of an accurate elevator setting recorder.
The Henderson "Hendy" 302 Cabin Airplane (British): A Two-Seat Low-Wing Cantilever Monoplane: Circular presenting a description of the Hendy 302, which is a two-seat, low-wing cantilever monoplane with a hinged cabin top. A description of the design, flying qualities, and photographs are provided.
An Investigation of Airplane Landing Speeds: "This paper describes an investigation on airplane landing speeds which was made to determine the applicability of accepted aerodynamic theory to the prediction of this particular performance characteristic. The experimental work consisted in measuring the landing speed of several monoplanes by a new photographic method. The results of these tests supplemented by available information regarding biplanes were compared with predictions made with basic aerodynamic theory" (p. 1).
Load Assumptions for Calculating the Strength of Airplanes: "The following load assumptions shall be taken as the basis of the strength calculations. Certain definite load conditions (e.g. of flight, control, landing and transport) shall be assumed. The loads shall be assumed to be safe loads, constant or only slowly variable, and the inertia forces due to elastic deformation are accordingly disregarded. The external forces, the force of gravity and the inertia forces on the whole airplane shall produce a condition of equilibrium" (p. 1).
Rolling Moments Due to Rolling and Yaw for Four Wing Models in Rotation: "This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of the rotating wings up to large angles of attack" (p. 301).
Effect of variation of chord and span of ailerons on hinge moments at several angles of pitch: This report presents the results of an investigation of the hinge moments of ailerons of various chords and spans on two airfoils having the Clark Y and USA-27 wing sections, supplementing the investigations described in NACA-TR-298 and NACA-TR-343, of the rolling and yawing moments due to similar ailerons on these two airfoil sections. 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.
Calculation of Tapered Monoplane Wings: The tapered wing shape increases the lift in the middle of the wing and thus reduces the bending moment of the lifting forces in the plane of symmetry. Since this portion of the wing is the thickest, the stresses of the wing material are reduced and desirable space is provided for stowing the loads in the wing. This statically excellent form of construction, however, has aerodynamic disadvantages which must be carefully weighed, if failures are to be avoided. This treatise is devoted to the consideration of these problems.

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