National Advisory Committee for Aeronautics (NACA) - 1,346 Matching Results

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Annual Report of the National Advisory Committee for Aeronautics (16th). Administrative Report Including Technical Reports Nos. 337 to 364: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (17th). Administrative Report Including Technical Report Nos. 365 to 400: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (18th). Administrative Report Including Technical Report Nos. 401 to 440: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (19th). Administrative Report Including Technical Report Nos. 441 to 474: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (20th). Administrative Report Including Technical Report Nos. 475 to 507: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (21st). Administrative Report Including Technical Report Nos. 508 to 541: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (22nd). Administrative Report Including Technical Report Nos. 542 to 576: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (23rd). Administrative Report Including Technical Report Nos. 577 to 611: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Annual Report of the National Advisory Committee for Aeronautics (24th). Administrative Report Including Technical Report Nos. 612 to 644: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
The apparent width of the plate in compression: This report discusses an investigation that treats the load capacity of a rectangular plate stressed in compression on one direction (x) beyond the buckling limit and the plate is rotatable (i.e., free from moments) supported at all four sides by bending-resistant beams.
Application and testing of transparent plastics used in airplane construction: This report discusses the efforts being made to remove the source of danger to passengers arising from the fracturing of silicate glass and some of the alternatives presented include: single-layer safety glass, multi-layer safety glass, transparent plastic resins.
The application of basic data on planing surfaces to the design of flying-boat hulls: From Introduction: "This report is concerned with the presentation of planning data in a form that facilities direct application to the initial stage of design."
Application of Practical Hydrodynamics to Airship Design: The purpose of the first two parts of this report is to present in concise format all the formulas required for computation of the hydrodynamic forces, so that they can be easily computed for either straight or curvilinear flight. Improved approximations are also introduced having a high degree of accuracy throughout the entire range of practical proportions. The remaining two parts of the report are devoted respectively to stability and skin friction, as functions of the same hydrodynamic forces.
Application of the Theory of Free Jets: Based upon Kirchoff's theory of free jets the flow through different screen arrangements of flat plates, as chiefly encountered with turbines in the cavitation zone is defined. It is shown by experiments that these theoretical results are very well representative in most cases of the conditions of discharge from water in air and consequently by cavitation. In addition, the experiments reveal a picture of the discrepancies between the actual flow and the theory of discharge of air in air (of water in water without cavitation).
An Application of the Von Kármán-Millikan Laminar Boundary-Layer Theory and Comparison With Experiment: Note presenting the von Kármán-Millikan theory of laminar boundary layers as applied to the laminar boundary layer about an elliptical cylinder on which boundary-layer and pressure-distribution measurements. Good agreement is obtained between calculated and experimental results, meaning that the method may be generally applied to the laminar boundary layer about any body provided that an experimentally determined pressure distribution is available.
Approximate Calculation of Multispar Cantilever and Semicantilever Wings With Parallel Ribs Under Direct and Indirect Loading: A method is presented for approximate static calculation, which is based on the customary assumption of rigid ribs, while taking into account the systematic errors in the calculation results due to this arbitrary assumption. The procedure is given in greater detail for semicantilever and cantilever wings with polygonal spar plan form and for wings under direct loading only. The last example illustrates the advantages of the use of influence lines for such wing structures and their practical interpretation.
An approximate spin design criterion for monoplanes: "A quantitative criterion of merit has been needed to assist airplane designers to incorporate satisfactory spinning characteristics into new designs. An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, has been formulated in a recent British report. In the present paper, the British results have been analyzed and applied to American designs. A simpler design criterion based solely on the type and the dimensions of the tail, has been developed: it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning" (p. 1).
An Approximate Spin Design Criterion for Monoplanes: "An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, was formulated. The British results were analyzed and applied to American designs. A simpler design criterion, based solely on the type and the dimensions of the tail, was developed; it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning" (p. 1).
Approximate Stress Analysis of Multistringer Beams With Shear Deformation of the Flanges: "The problem of the skin-stringer combinations used as axially loaded panels or as covers for box beams is considered from the point of view of the practical stress analyst. By a simple substitution the problem is reduced to the problem of the single-stringer structure, which has been treated in NACA Report no. 608. The method of making this substitution is essentially empirical; in order to justify it, comparisons are shown between calculations and strain-gage tests of three beams tested by the author and of one compression panel and three beams tested and reported elsewhere" (p. 469).
Armstrong Whitworth 27 "Ensign" Commercial Airplane (British): An All-Metal High-Wing Monoplane: Circular presenting a description of the Armstrong Whitworth monoplane, which is an all-metal, high-wing monoplane with landing gear that retracts into the wing-mounted engine nacelles. Details of the wings, wing spars, fuselage, controls, engines, speeds, drawings, and photographs are provided.
Armstrong-Whitworth A.W. 15 "Atlanta" Airplane (British): A Commercial Multiplace Cantilever Monoplane: Circular describing the Armstrong Whitworth XV "Atalanta" airplane, which is a commercial multiplace cantilever monoplane. Details of the wings, landing gear, fuselage, control surfaces, structural design, wing, engine, characteristics, drawings, and photographs are provided.
The Armstrong Whitworth A.W. 16 Military Airplane (British): A Single-Seat Biplane: Circular presenting a description of the A.W. XVI, which is a single-bay staggered biplane of metal construction with a clean external design. A description of the tail unit, control system, cockpit, fuselage, characteristics, performance, drawings, and photographs are provided.
Attaining a Steady Air Stream in Wind Tunnels: "Many experimental arrangements of varying kind involve the problems of assuring a large, steady air stream both as to volume and to time. For this reason a separate discussion of the methods by which this is achieved should prove of particular interest. Motors and blades receive special attention and a review of existent wind tunnels is also provided" (p. 1).
Auto-Ignition and Combustion of Diesel Fuel in a Constant-Volume Bomb: Report presents the results of a study of variations in ignition lag and combustion associated with changes in air temperature and density for a diesel fuel in a constant-volume bomb. The test results have been discussed in terms of engine performance wherever comparisons could be drawn. The most important conclusions drawn from this investigation are: the ignition lag was essentially independent of the injected fuel quantity. Extrapolation of the curves for the fuel used shows that the lag could not be greatly decreased by exceeding the compression-ignition engines. In order to obtain the best combustion and thermal efficiency, it was desirable to use the longest ignition lag consistent with a permissible rate of pressure rise.
Automatic Stability of Airplanes: It is endeavored in this report to give a full outline of the problem of airplane stability and to classify the proposed solutions systematically. Longitudinal stability, which can be studied separately, is considered first. The combination of lateral and directional stabilities, which cannot be separated, will be dealt with later.
Automatic Stabilization: This report lays more stress on the principles underlying automatic piloting than on the means of applications. Mechanical details of servomotors and the mechanical release device necessary to assure instantaneous return of the controls to the pilot in case of malfunction are not included. Descriptions are provided of various commercial systems.
Automatic Stabilization: This report concerns the study of automatic stabilizers and extends it to include the control of the three-control system of the airplane instead of just altitude control. Some of the topics discussed include lateral disturbed motion, static stability, the mathematical theory of lateral motion, and large angles of incidence. Various mechanisms and stabilizers are also discussed.
The Automotive Ignition Coil: This report gives the results of a series of measurements on the secondary voltage induced in an ignition coil of typical construction under a variety of operating conditions. These results show that the theoretical predictions hitherto made as to the behavior of this type of apparatus are in satisfactory agreement with the observed facts. The large mass of data obtained is here published both for the use of other investigators who may wish to compare them with other theoretical predictions and for the use of automotive engineers who will here find definite experimental results showing the effect of secondary capacity and resistance on the crest voltage produced by ignition apparatus.
The Avia 51 Commercial Airplane (Czechoslovakian): A Cantilever High-Wing Monoplane: Circular describing the Avia 51 commercial airplane, which is a Czechoslovakian cantilever high-wing monoplane with a fairly orthodox design. Details of the performance, construction, wing, ailerons, fuselage, landing gear, engines, characteristics, drawings, and photographs are provided.
The Avro 627 "Mailplane" (English): A Single-Seat Biplane: Circular describing the Avro 627 Hailplane, which is a single-seat biplane designed for delivering air mail. Details regarding the fuselage, wings, tail, landing gear, power installation, characteristics, performance, drawings, and photographs are provided.
The Avro 631 Training Airplane (British): A Two-Seat Light Biplane: Circular describing the Avro 631 training airplane, which is a British two-seat light biplane that is meant to be affordable and small. Details regarding the wings, fuselage, tail unit, landing gear, power plant, accommodation, characteristics, performance, drawings, and photographs are provided.
Avro 642 Commercial Airplane (British): A High-Wing Cantilever Monoplane: Circular describing the Avro 642, which is a mixed construction high-wing cantilever monoplane. Details of the engines, controls, interior, wings, cockpit, ailerons, landing gear, characteristics, performance, drawings, and photographs are provided.
The Avro "Anson" General-Purpose Airplane (British): A Two-Engine Low-Wing Cantilever Monoplane: Circular describing the Avro Anson, which is a two-engine low-wing cantilever monoplane of the general-purpose type. Details regarding the wing, landing gear, controls, fuselage, pilot's equipment, power plant, armament, characteristics, performance, drawings, and photographs are provided.
Avro C.30 Direct-Control Autogiro (British): Circular describing the Avro C.30 direct-control autogiro. Details of the construction, fuselage, engine mounting, tail, cockpits, rotor system, characteristics, performance, drawings, and photographs are provided.
The Avro "Commodore" Touring Airplane (British): A Cabin Biplane: Circular describing the Avro Commodore, which is a cabin biplane of metal construction that is designed for comfort rather than performance. Details regarding the fuselage, wings, landing gear, controls, characteristics, drawings, and photographs are provided.
The "Avro Trainer" Airplane (British): A Training Biplane: Circular presenting a description of the Avro Trainer airplane, which is primarily intended for pilots in training and is designed to be easy to use, including large, comfortable cockpits, good view, effective windshields, and wide track. Details of the design, flight characteristics, drawings, and photographs are provided.
Balanced and Servo Control Surfaces: "Many reports on various control systems are available, but the results cannot be generally applied since the effect of particular changes of surface-form and mounting are subject to variations depending upon airfoil section and influences of airplane layout. This report presents a simple analysis of several control systems in more general use. Elevators, ailerons, and rudders are all discussed" (p. 1).
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.
Basic Requirements of Fuel-Injection Nozzles for Quiescent Combustion Chambers: This report presents test results obtained during an investigation of the performance of a single-cylinder, high-speed, compression-ignition test engine when using multiple-orifice fuel-injection valve nozzles in which the number and the direction of the orifices were varied independently.
Baynes Bee Light Airplane (British): A Two-Seat High-Wing Monoplane: Circular presenting a description of the Baynes Bee, which is a light two-seat high-wing monoplane. Details of its unique qualities, design, components, flying qualities, drawings, and photographs are provided.
Behavior of a Plate Strip Under Shear and Compressive Stresses Beyond the Buckling Limit: The present report is an extension of previous theoretical investigations on the elastic behavior of a plate under compression and shear in the region above the critical. The main object is the clarification of the behavior immediately above the buckling limit since no theoretical expressions for this range have thus far been found and since experimentally, too, any degree of regularity in the behavior of the plate in the range between the critical load and about three to four times the critical, is discernible only with difficulty.
The Behavior of Conventional Airplanes in Situations Thought to Lead to Most Crashes: Simple flight tests were made on ten conventional airplanes for the purpose of determining their action in two situations, which are generally thought to precede and lead to a large proportion of airplane crashes. These situations are when in an attempt to stretch the glide in a forced landing, the airplane is stalled, and when while taking off, particularly if taking off steeply, the engine fails at a low altitude.
Behavior of Static Pressure Heads at High Speeds: "Memorandum presenting the development of a static pressure head for high speeds. These tests proved the practicability of static pressure heads at speeds up to 400 km/h (248.5 mph). It weighs 6.5 kg or 2.5 times as much as the old head. The position of the pressure head below the airplane was determined by bearing method at different speeds and for different lengths of suspension" (p. 1).
The Behavior of Thin-Will Monocoque Cylinders Under Torsional Vibration: "Curves of forced frequency against amplitude are presented for the conditions where the forced frequency is both increased and decreased into the resonant range. On the basis of these curves it is shown that the practical resonance frequency is the point where wrinkling first occurs and that the resonance frequency will be subject to considerable travel once permanent wrinkles appear in the vibrating shell. The decreasing mode of striking resonance is found to be by far the most destructive condition" (p. 1).
Behavior of Turbulent Boundary Layers on Curved Convex Walls: The system of linear differential equations which indicated the approach of separation and the so-called "boundary-layer thickness" by Gruschwitz is extended in this report to include the case where the friction layer is subject to centrifugal forces. Evaluation of the data yields a strong functional dependence of the momentum change and wall drag on the boundary-layer thickness radius of curvature ratio for the wall. It is further shown that the transition from laminar to turbulent flow occurs at somewhat higher Reynolds Numbers at the convex wall than at the flat plate, due to the stabilizing effect of the centrifugal forces.
Behavior of Vortex Systems: Progressive application of the Kutta-Joukowsky theorem to the relationship between airfoil lift and circulation affords a number of formulas concerning the conduct of vortex systems. The application of this line of reasoning to several problems of airfoil theory yields an insight into many hitherto little observed relations. This report is confined to plane flow, hence all vortex filaments are straight and mutually parallel (perpendicular to the plane of flow).
The Behavior Under Shearing Stress of Duralumin Strip With Round, Flanged Holes: "This report presents the results of an investigation to determine the behavior of dural strip with flanged holes in the center when subjected to shear stresses. They buckle under a certain load just as a flat sheet. There is one optimum hole spacing and a corresponding buckling load in shear for each sheet width, sheet thickness, and flange form. Comparison with non-flanged sheets revealed a marked increase of buckling load in shear due to the flanging and a slightly greater displacement" (p. 1).
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.
Bending of Beams of Thin Sections: The tendency toward economy of material and lightness of structure has long since led to the increased application of beams having large ratios of moment of area W to cross-sectional area F. This paper tries to provide an answer to how thin the beams can be.
The Bending of Beams With Thin Tension Flanges: This report analyzes the action of a cantilever T beam with a tension flange so thin it can only carry tensile stresses.

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