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  • Other Sources  (135)
  • NASA Technical Reports  (135)
  • 1930-1934
  • 1925-1929  (135)
  • 1928  (135)
Collection
  • Other Sources  (135)
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  • 1930-1934
  • 1925-1929  (135)
Year
  • 1
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    Aeroelastic stability of wind turbine blades (1928)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The second degree nonlinear aeroelastic equations for a flexible, twisted, nonuniform wind turbine blade were developed using Hamilton's principle. The derivation of these equations has its basis in the geometric nonlinear theory of elasticity. These equations with periodic coefficients are suitable for determining the aeroelastic stability and response of large wind turbine blades. Methods for solving these equations are discussed.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Res. Center Wind Turbine Structural Dyn.; p 61-69
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  • 2
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    Bibliography of Aeronautics: 1926 (1928)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: This Bibliography of Aeronautics for 1926 covers the aeronautical literature published from January 1 to December 31, 1926. The first Bibliography of Aeronautics was published by the Smithsonian Institution as volume 55 of the Smithsonian Miscellaneous Collections and covered the material published prior to June 30, 1909. Supplementary volumes of the Bibliography of Aeronautics for the subsequent years have been published by the National Advisory Committee for Aeronautics. The last preceding volume was for the calendar year 1925. As in the previous volumes, citations of the publications of all nations are included in the languages in which these publications originally appeared. The arrangement is dictionary form with author find subject entry, and one alphabetical arrangement. Detail in the matter of subject reference has been omitted on aCC01.mt of the cost of presentation, but an attempt has been made to give sufficient cross reference for research in special lines.
    Keywords: Aeronautics (General)
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  • 3
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    Bibliography of Aeronautics: 1928 (1928)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: This Bibliography of Aeronautics for 1928 covers the aeronautical literature published from January 1 to December 31, 1928. The first Bibliography of Aeronautics was published by the Smithsonian Institution as volume 55 of the Smithsonian Miscellaneous Collections and covered the material published prior to June 30, 1909. Supplementary volumes of the Bibliography of Aeronautics for the subsequent years have been published by the National Advisory Committee for Aeronautics. The last preceding volume was for the calendar year 1927. As in the previous volumes, citations of the publications of all nations are included in the languages in which these publications originally appeared. The arrangement is in dictionary form with author and subject entry, and one alphabetical arrangement. Detail in the matter of subject reference has been omitted on account of the cost of presentation, but an attempt has been made to give sufficient cross reference for research in special lines.
    Keywords: Aeronautics (General)
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  • 4
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    The Measurement of Pressure Through Tubes in Pressure Distribution Tests (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this report were made to determine the error caused by using small tubes to connect orifices on the surface of aircraft to central pressure capsules in making pressure distribution tests. Aluminum tubes of 3/16-inch inside diameter were used to determine this error. Lengths from 20 feet to 226 feet and pressures whose maxima varied from 2 inches to 140 inches of water were used. Single-pressure impulses for which the time of rise of pressure from zero to a maximum varied from 0.25 second to 3 seconds were investigated. The results show that the pressure recorded at the capsule on the far end of the tube lags behind the pressure at the orifice end and experiences also a change in magnitude. For the values used in these tests the time lag and pressure change vary principally with the time of rise of pressure from zero to a maximum and the tube length. Curves are constructed showing the time lag and pressure change. Empirical formulas are also given for computing the time lag. Analysis of pressure distribution tests made on airplanes in flight shows that the recorded pressures are slightly higher than the pressures at the orifice and that the time lag is negligible. The apparent increase in pressure is usually within the experimental error, but in the case of the modern pursuit type of airplane the pressure increase may be 5 per cent. For pressure-distribution tests on airships the analysis shows that the time lag and pressure change may be neglected.
    Type: NACA-TR-270
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  • 5
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    Factors in the Design of Centrifugal Type Injection Valves for Oil Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This research was undertaken in connection with a general study of the application of the fuel injection engine to aircraft. The purpose of the investigation was to determine the effect of four important factors in the design of a centrifugal type automatic injection valve on the penetration, general shape, and distribution of oil sprays. The general method employed was to record the development of single sprays by means of special high-speed photographic apparatus capable of taking 25 consecutive pictures of the moving spray at a rate of 4,000 per second. Investigations were made concerning the effects on spray characteristics, of the helix angle of helical grooves, the ratio of the cross-sectional area of the orifice to that of the grooves, the ratio of orifice length to diameter, and the position of the seat. Maximum spray penetration was obtained with a ratio of orifice length to diameter of about 1.5. Slightly greater penetration was obtained with the seat directly before the orifice.
    Type: NACA-TR-268
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  • 6
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    Characteristics of propeller sections tested in the variable density wind tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were carried out in the variable density wind tunnel of the National Advisory Committee for Aeronautics on six airfoil sections used by the Bureau of Aeronautics as propeller sections. The sections were tested at pressures of 1 and 20 atmospheres corresponding to Reynolds numbers of about 170,000 and 3,500,000. The results obtained, besides providing data for the design of propellers, should be of special interest because of the opportunity afforded for the study of scale effect on a family of airfoil sections having different thickness ratios. (author)
    Type: NACA-TR-259
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  • 7
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    Pressure Distribution over a Wing and Tail Rib of a VE-7 and of a TS Airplane in Flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made to determine the pressure distribution over a rib of the wing and over a rib of the horizontal tail surface of an airplane in flight and to obtain information as to the time correlation of the loads occurring on these ribs. Two airplanes, VE-7 and TS, were selected in order to obtain the information for a thin and a thick wing section. In each case the pressure distribution was recorded for the full range of angle of attack in level flight and throughout violent maneuvers. The results show: (a) that the present rib load specifications in use by the Army Air Corps and the Bureau of Aeronautics, Navy Department, are in fair agreement with the loads actually occurring in flight, but could be slightly improved; (b) that there appears to be no definite sequence in which wing and tail surface ribs reach their respective maximum loads in different maneuvers; (c) that in accelerated flight, at air speeds less than or equal to 60 per cent of the maximum speed, the accelerations measured agree very closely with the theoretically possible maximum accelerations. In maneuvers at higher air speeds the observed accelerations were smaller than those theoretically possible. (author)
    Type: NACA-TR-257
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  • 8
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    Preliminary biplane tests in the variable density wind tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Biplane cellules using the N.A.C.A.-M6 airfoil section have been tested in the variable density wind tunnel of the National Advisory Committee for Aeronautics. Three cellules, differing only in the amount of stagger, were tested at two air densities, corresponding to pressures of one atmosphere and of twenty atmospheres. The range of angle of attack was from -2 degrees to +48 degrees. The effect of stagger on the lift and drag, and on the shielding effect of the upper wing by the lower at high angles of attack was determined.
    Type: NACA-TN-289
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  • 9
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    The reaction on a float bottom when making contact with water at high speeds (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted to investigate the possibility of a serious accident arising from unintentional contact with the water in substantially horizontal flight at high speed. Referring to vector diagrams on Figure 2, it will be seen that a very dangerous condition may arise if the float be allowed to come in contact with the water at high speeds as, for example, when flying at high speed just above the water. The initial diving moment due to suction and drag combined may be great enough to cause the seaplane to nose under before the pilot is able to control the motion. The same test data indicate clearly the existence of forces and moments tending to produce the phenomenon observed by Mr. Carroll (Technical Note No. 287) when the maneuver is carried out at lower speeds, as in a landing.
    Type: NACA-TN-288
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  • 10
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    A dangerous seaplane landing condition (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A peculiar phenomena in seaplane landing is observed and reported. The seaplane having executed a normal fast landing at low incidence, a forward movement of the control stick effected an unusual condition in that the seaplane left the water suddenly in an abnormal attitude. The observations describing this phenomena are offered as a warning against possible accident and as a conjectural cause of seaplane landing accidents of a certain kind.
    Type: NACA-TN-287
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  • 11
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    Preliminary Investigation on Boundary Layer Control by Means of Suction and Pressure with the U.S.A. 27 Airfoil (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this report constitute a preliminary investigation of airfoil boundary layer control, as carried out in the atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory, from February to August, 1927. Tests were made on a U.S.A. 27 airfoil section with various slot shapes and combinations, and at various amounts of pressure or suction on the slots. The lift of airfoils can be increased by removing or by accelerating the boundary layer. Removing the boundary layer by suction is more economical than to accelerate it by jet action. Gauze-covered suction slots apparently give the best results. When not in operation, all suction slots tested had a detrimental effect upon the aerodynamic characteristics of the airfoil which was not apparent with the backward-opening pressure slots. Thick, blunt-nose airfoils would seem to give best results with boundary layer control.
    Type: NACA-TN-286
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  • 12
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    Corrosion Embrittlement of Duralumin IV : The Use of Protective Coatings (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Although the corrosion resistance of sheet duralumin can be greatly improved by suitable heat treatment, protection of the surface is still necessary if long life under varied service conditions is to be insured. The coatings used for this purpose may be grouped into three classes: the varnish type of coating, the oxide type produced by a chemical treatment of the surface, and metallic coatings, of which aluminum appears to be the most promising. Since the necessary weather exposure tests are not complete, some of the conclusions regarding the value of various surface coatings are necessarily tentative.
    Type: NACA-TN-285
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  • 13
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    Corrosion Embrittlement of Duralumin III Effect of the Previous Treatment of Sheet Material on the Susceptibility to This Type of Corrosion (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a result of testing, it was determined that control of the rate of quenching and the avoidance of accelerated aging by heating are the only means of modifying duralumin itself so as to minimize the intercrystalline form of corrosive attack. It is so simple a means that it should be adopted even though it may not completely prevent, but only reduce, this form of corrosive attack. By so doing, the need for protection of the surface is less urgent.
    Type: NACA-TN-284
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  • 14
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    Corrosion Embrittlement of Duralumin II Accelerated Corrosion Tests and the Behavior of High-Strength Aluminum Alloys of Different Compositions (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The permanence, with respect to corrosion, of light aluminum alloy sheets of the duralumin type, that is, heat-treatable alloys containing Cu, Mg, Mn, and Si is discussed. Alloys of this type are subject to surface corrosion and corrosion of the interior by intercrystalline paths. Results are given of accelerated corrosion tests, tensile tests, the effect on corrosion of various alloying elements and heat treatments, electrical resistance measurements, and X-ray examinations.
    Type: NACA-TN-283
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  • 15
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    Corrosion Embrittlement of Duralumin I Practical Aspects of the Problem (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Since aircraft design is tending toward all-metal construction, the strong heat-treatable light aluminum alloy, duralumin (a generic name for a class of heat-treatable alloys containing Cu, Mg, Mn, and Si), is finding increasing application. Doubt has been expressed concerning the reliability and permanence of these materials. Information is given on the effect of corrosion on the tensile properties of 14-gauge sheet duralumin, heat treated by quenching in hot water after being heated for 15 minutes in a fused nitrate bath at 500 to 510 C. Intercrystalline corrosion and practical aspects of intercrystalline embrittlement are discussed with respect to duralumin.
    Type: NACA-TN-282
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  • 16
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    A Comparison of Propeller and Centrifugal Fans for Circulating the Air in a Wind Tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this paper afford a direct comparison of the efficiency and smoothness of flow obtained with propeller fan and multiblade centrifugal fan drives in the same wind tunnel. The propeller fan was found to be superior to the centrifugal fan in that the efficiency was about twice as great, and the flow much smoother.
    Type: NACA-TN-281
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  • 17
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    Drag and Cooling with Various Forms of Cowling for a Whirlwind Engine in a Cabin Fuselage (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation on the cowling of radial air-cooled engines was conducted in the 20-foot Propeller Research Tunnel at Langley Field. Cooling and drag tests were made with each form of cowling. The propulsive efficiency was found to be practically the same with all forms of cowling.
    Type: NACA-TN-301
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  • 18
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    Drag of Exposed Fittings and Surface Irregularities on Airplane Fuselages (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements of drag were made on fittings taken from a typical fuselage to determine whether the difference between the observed full size fuselage drag and model fuselage drag could be attributed to the effects of fittings and surface irregularities found on the full size fuselage and not on the model. There are wide variations in the drag coefficients for the different fittings. In general those which protrude little from the surface or are well streamlined show very low and almost negligible drag. The measurements show, however, that a large part of the difference between model and full scale test results may be attributed to these fittings.
    Type: NACA-TN-280
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  • 19
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    The variation in pressures in the cockpit fan airplane in flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of an investigation to determine the pressures in the open cockpit of a Vought VE-7 airplane are given. The observed values are small and the effect upon instruments is inconsiderable.
    Type: NACA-TN-300
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  • 20
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    Resistance of streamline wires (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note contains the results of tests to determine the resistance of four sizes of streamline wire. The investigation was conducted in the six-inch wind tunnel of the National Advisory Committee for Aeronautics. The tests were made at various velocities and it was found that the resistance of streamline wires was considerably less than that of round wires of equivalent strength. Scale effect was also found since, with an increase of Reynolds Number, a decrease in the resistance coefficient was obtained.
    Type: NACA-TN-279
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  • 21
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    The Effect of Fillets Between Wings and Fuselage on the Drag and Propulsive Efficiency of an Airplane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made to determine the effect of fillets between wings and fuselage on the drag and propulsive efficiency of a high-wing cabin monoplane. These tests were made in the 20-foot Propeller Research Tunnel of the National Advisory Committee for Aeronautics.
    Type: NACA-TN-299
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  • 22
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    The Determination of Several Spray Characteristics of a High-Speed Oil Engine Injection System with an Oscilloscope (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to determine the injection lag, duration of injection, and spray start and cut-off characteristics of a fuel injection system operated on an engine and injecting fuel into the atmosphere.
    Type: NACA-TN-298
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  • 23
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    An Automatic Speed Control for Wind Tunnels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Described here is an automatic control that has been used in several forms in wind tunnels at the Washington Navy Yard. The form now in use with the 8-foot tunnel at the Navy Yard is considered here. Details of the design and operation of the automatic control system are given. Leads from a Pitot tube are joined to an inverted cup manometer located above a rheostat. When the sliding weight of this instrument is set to a given notch, say for 40 m.p.h, the beam tip vibrates between two electric contacts that feed the little motor. Thus, when the wind is too strong or too weak, the motor automatically throws the rheostat slide forward and backward. If it failed to function well, the operator would notice the effect on his meniscus, and would operate the hand control by merely pressing the switch.
    Type: NACA-TN-278
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  • 24
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    Pressure distribution on wing ribs of the VE-7 and TS airplanes in flight Part II : pull-ups (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the second of a series of notes, each of which presents the complete results of pressure distribution tests made at Langley Field by the National Advisory Committee for Aeronautics, on wing and tail ribs of the VE-7 and TS airplanes for a particular maneuver of flight. The results for pull-ups are presented in the form of curves which show the variation of pressure distribution, total loads, normal acceleration and center of pressure with respect to time.
    Type: NACA-TN-277
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  • 25
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    Preliminary report on the flat-top lift curve as a factor in control at low speed (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the importance of the flat-top lift curve as a factor contributing to safety and control at low speed. An analysis of existing airfoil data indicated definite relations between the shape of the lift curve and certain section dimensions.
    Type: NACA-TN-297
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  • 26
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    Helium tables. (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These tables are intended to provide a standard method and to facilitate the calculation of the quantity of "Standard Helium" in high pressure containers. The research data and the formulas used in the preparation of the tables were furnished by the Research Laboratory of Physical Chemistry, of the Massachusetts Institute of Technology.
    Type: NACA-TN-276
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  • 27
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    Bearing strength of wood under steel aircraft bolts and washers and other factors influencing fitting design (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this report is to correlate, bring up to date, and put under a single cover all the information thought to be essential to an understanding of the formulas.
    Type: NACA-TN-296
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  • 28
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    Determination of Propeller Deflection by Means of Static Load Tests on Models (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note describes a simple and inexpensive method for determining the deflection of propeller blades under operating loads. Both the centrifugal force and air force loads are applied statically as a number of concentrated loads by means of weights and wires. Two methods of attaching the wires to the propeller blades have been tested, both giving approximately the same deflections. The method is considered useful for studying the deflections of propellers of different shapes under various operating conditions.
    Type: NACA-TN-275
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  • 29
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    The effect of tip shields on a horizontal tail surface (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of experiments made in the wind tunnel of the Daniel Guggenheim School of Aeronautics, New York University, on the effect of tip shields on a horizontal tail surface are described and discussed. It was found that some aerodynamic gain can be obtained by the use of tip shields though it is considered doubtful whether their use would be practical.
    Type: NACA-TN-295
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  • 30
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    The Effect of the Sperry Messenger Fuselage on the Air Flow at the Propeller Plane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to study the effect of the fuselage, landing gear, and engine on the air flow through the propeller, a survey was made in the plane of the Sperry Messenger propeller with the propeller removed. The tests were made in the 20-foot air stream of the propeller research tunnel of the National Advisory Committee for Aeronautics at Langley Field, Virginia. The variation of the velocity with distance from the center in the propeller plane was found to be appreciable and well worth consideration in the design of propellers. It was also found that the velocity through the propeller plane was affected by the presence of the engine, and that the velocity in front of the landing gear was lower than that at other points in the propeller plane having the same radius.
    Type: NACA-TN-274
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  • 31
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    The Drag of a J-5 Radial Air-Cooled Engine (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note describes tests of the drag due to a Wright "Whirlwind" (J-5) radial air-cooled engine mounted on a cabin type airplane. The tests were made in the 20-foot Propeller Research Tunnel of the National Advisory Committee for Aeronautics. The drag was obtained with three different types of exhaust stacks: Short individual stacks, a circular cross section collector ring, and a streamline cross section collector ring.
    Type: NACA-TN-292
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  • 32
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    Wind tunnel force tests in wing systems through large angles of attack (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Force tests on a systematic series of wing systems over a range of angle of attack from minus forty-five degrees to plus ninety degrees are covered in this report. The investigation was made on monoplane and biplane wing models to determine the effects of variations of tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweepback, and airfoil profile.
    Type: NACA-TN-294
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  • 33
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    The Effect on Performance of a Cutaway Center Section (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The assumption is made that a skeleton or cutaway center section is desirable for forward vision and to determine the effect of such mutilation upon performance the following work was done. The airplane used was a Vought VE-7 and in addition to the cutaway center section a system of end plates or fins was installed. Various conditions and combinations were investigated in level flight and in climb. It is found that the greatest difference in the conditions investigated was a drop of 12.5 per cent in a 10-minute climb while the effect upon level speeds was negligible.
    Type: NACA-TN-273
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  • 34
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    The Formation of Ice upon Exposed Parts of an Airplane in Flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to experimentally study the conditions leading to ice formation on aircraft surfaces, an aircraft was equipped with small auxiliary surfaces and aerodynamic shapes similar to struts, wires, Pitot heads, etc. This airplane was flown at an altitude where a temperature of 32 F was encountered, at such times as cloud formations could be found at the coincident altitude. Here it was discovered that ice formed rapidly in regard to quantity,character, shape, and rapidity of formation. An examination of this data, which confirms observations of pilots, indicates that the weight of ice collected can very possibly be sufficient to force the airplane to rapidly lose altitude on account of the increased loads. However, it is more evident that the malformation of the aerodynamic shapes may so increase the drag and reduce the lift so as to produce a loss of altitude even greater in consequence, the combination of the two working in the same direction having a double effect. Other adverse consequences are noted. The recommendation for the guidance of those who must encounter these conditions appears to lie entirely along the lines of avoidance.
    Type: NACA-TN-293
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  • 35
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    Special Propeller Protractor (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A special protractor was designed and built with a view towards supplying a simple, inexpensive, practical, portable instrument for making measurements to detect propeller warpage under practically all conditions, without the use of auxiliary equipment, and without having to remove the propeller from the airplane. A detailed description is given of the protractor. Techniques for measuring are described. Directions are given on how to use the protractor to set detachable blade-type propellers on an airplane.
    Type: NACA-TN-272
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  • 36
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    Full Scale Drag Tests on Various Parts of Sperry Messenger Airplane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag of a Sperry Messenger airplane with the wings removed, and also the drag of its various component parts, was measured in the 20-foot air stream of the N.A.C.A. propeller research tunnel at air speeds from 50 to 100 m.p.h. It was found that the three-cylinder radial air-cooled engine nearly doubled the drag of the bare fuselage, and the drag of the landing gear was about the same as that of the fuselage and engine combined.
    Type: NACA-TN-271
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  • 37
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    Gluing Practice at Aircraft Manufacturing Plants (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report records observations and recommendations resulting from an inspection trip to representative aircraft manufacturing establishments and repair stations. This inspection was made for the Navy Department and was specifically in reference to gluing practice at the various places visited. The period of the visits was between November 23, 1926 and February 16, 1927.
    Type: NACA-TN-291
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  • 38
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    Welding of high chromium steels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A brief description is given of different groups of high chromium steels (rustless iron and stainless steels) according to their composition and more generally accepted names. The welding procedure for a given group will be much the same regardless of the slight variations in chemical composition which may exist within a certain group. Information is given for the tensile properties (yield point and ultimate strength) of metal sheets and welds before and after annealing on coupons one and one-half inches wide. Since welds in rustless iron containing 16 to 18 percent chromium and 7 to 12 percent nickel show the best combination of strength and ductility in the 'as welded' or annealed condition, it is considered the best alloy to use for welded construction.
    Type: NACA-TN-290
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  • 39
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    Friction of Aviation Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The first portion of this report discusses measurements of friction made in the altitude laboratory of the Bureau of Standards between 1920 and 1926 under research authorization of the National Advisory Committee for Aeronautics. These are discussed with reference to the influence of speed, barometric pressure, jacket-water temperature, and throttle opening upon the friction of aviation engines. The second section of the report deals with measurements of the friction of a group of pistons differing from each other in a single respect, such as length, clearance, area of thrust face, location of thrust face, etc. Results obtained with each type of piston are discussed and attention is directed particularly to the fact that the friction chargeable to piston rings depends upon piston design as well as upon ring design. This is attributed to the effect of the rings upon the thickness and distribution of the oil film which in turn affects the friction of the piston to an extent which depends upon its design.
    Type: NACA-TR-262
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  • 40
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    Some Factors Affecting the Reproducibility of Penetration and the Cut-Off of Oil Sprays for Fuel-injection Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was undertaken at the Langley Memorial Aeronautical Laboratory in connection with a general research on fuel-injection for aircraft. The purpose of the investigation was to determine the factors controlling the reproducibility of spray penetration and secondary discharges after cut-off. The development of single sprays from automatic injection valves was recorded by means of special high-speed photographic apparatus capable of taking 25 consecutive pictures of the moving spray at a rate of 4,000 per second. The effect of two types of injection valves, injection-valve tube length, initial pressure in the injection-valve tube, speed of the injection control mechanism, and time of spray cut-off, on the reproducibility of spray penetration, and on secondary discharges were investigated. It was found that neither type of injection valve materially affected spray reproducibility. The initial pressure in the injection-valve tube controlled the reproducibility of spray penetrations. An increase in the initial pressure or in the length of the injection-valve tube slightly increased the spray penetration within the limits of this investigation. The speed of the injection-control mechanism did not affect the penetration. Analysis of the results indicates that secondary discharges were caused in this apparatus by pressure waves initiated by the rapid opening of the cut-off valve. The secondary discharges were eliminated in this investigation by increasing the length of the injection-valve tube. (author)
    Type: NACA-TR-258
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  • 41
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    Tests on Models of Three British Airplanes in the Variable Density Wind Tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the results of tests made in the National Advisory Committee for Aeronautics variable density wind tunnel on three airplane models supplied by the British Aeronautical Research Committee. These models, the BE-2E with R.A.F. 19 wings, the British Fighter with R.A.F. 15 wings, and the Bristol Fighter with R.A.F. 30 wings, were tested over a wide range in Reynolds numbers in order to supply data desired by the Aeronautical Research Committee for scale effect studies. The maximum lifts obtained in these tests are in excellent agreement with the published results of British tests, both model and full scale. No attempt is made to compare drag data, owing to the emission of tail surfaces, radiator, etc., from the model, but is shown that the scale effect observed on the drag coefficients in these tests is due to a large extent to the parts of the models other than the wings. (author)
    Type: NACA-TR-279
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  • 42
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    The Gaseous Explosive Reaction : The Effect of Inert Gases (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Attention is called in this report to previous investigations of gaseous explosive reactions carried out under constant volume conditions, where the effect of inert gases on the thermodynamic equilibrium was determined. The advantage of constant pressure methods over those of constant volume as applied to studies of the gaseous explosive reaction is pointed out and the possibility of realizing for this purpose a constant pressure bomb mentioned. The application of constant pressure methods to the study of gaseous explosive reactions, made possible by the use of a constant pressure bomb, led to the discovery of an important kinetic relation connecting the rate of propagation of the zone of explosive reaction within the active gases, with the initial concentrations of those gases: s = K(sub 1)(A)(sup n1)(B)(sup n2)(C)(sup n3)------. By a method analogous to that followed in determining the effect of inert gases on the equilibrium constant K, the present paper records an attempt to determine their kinetic effect upon the expression given above.
    Type: NACA-TR-280
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  • 43
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    Propeller problems (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report tries to give a comprehensive survey of the most important propeller problems such as the shape of propellers and the effect of atmospheric conditions on propeller performance.
    Type: NACA-TM-491
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  • 44
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    Aerodynamic characteristics of thin empirical profiles and their application to the tail surfaces and ailerons of airplanes (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-493
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  • 45
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    Characteristics of Five Propellers in Flight (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made for the purpose of determining the characteristics of five full-scale propellers in flight. The equipment consisted of five propellers in conjunction with a VE-7 airplane and a Wright E-2 engine. The propellers were of the same diameter and aspect ratio. Four of them differed uniformly in thickness and pitch and the fifth propeller was identical with one of the other four with exception of a change of the airfoil section. The propeller efficiencies measured in flight are found to be consistently lower than those obtained in model tests. It is probable that this is mainly a result of the higher tip speeds used in the full-scale tests. The results show also that because of differences in propeller deflections it is difficult to obtain accurate comparisons of propeller characteristics. From this it is concluded that for accurate comparisons it is necessary to know the propeller pitch angles under actual operating conditions. (author)
    Type: NACA-TR-292
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  • 46
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    Differential Pressures on a Pitot-venturi and a Pitot-static Nozzle over 360 Degrees Pitch and Yaw (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements of the differential pressures on two navy air-speed nozzles, consisting of a Zahm type Pitot-Venturi tube and a SQ-16 two-pronged Pitot-static tube, in a tunnel air stream of fixed speed at various angles of pitch and yaw between 0 degrees and plus or minus 180 degrees. This shows for a range over -20 degrees to +20 degrees pitch and yaw, indicated air speeds varying very slightly over 2 per cent for the Zahm type and a maximum of about 5 per cent for the SQ-16 type from the calibrated speed at 0 degree. For both types of air-speed nozzle the indicated air speed increases slightly as the tubes are pitched or yawed several degrees from their normal 0 degrees altitude, attains a maximum around plus or minus 15 degrees to 25 degrees, declines rapidly therefrom as plus or minus 40 degrees is passed, to zero in the vicinity of plus or minus 70 degrees to 100 degrees, and thence fluctuates irregular from thereabouts to plus or minus 180 degrees. The complete variation in indicated air speed for the two tubes over 360 degree pitch and yaw is graphically portrayed in figures 9 and 10. For the same air speed and 0 degree pitch and yaw the differential pressure of the Zahm type Pitot-Venturi nozzle is about seven times that of the SQ-16 type two-prolonged Pitot-static nozzle.
    Type: NACA-TR-264
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  • 47
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    Performance of Several Combustion Chambers Designed for Aircraft Oil Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several investigations have been made on single-cylinder test engines to determine the performance characteristics of four types of combustion chambers designed for aircraft oil engines. Two of the combustion chambers studied were bulb-type precombustion chambers, the connecting orifice of one having been designed to produce high turbulence by tangential air flow in both the precombustion chamber and the cylinder. The other two were integral combustion chambers, one being dome-shaped and the other pent-roof shaped. The injection systems used included cam and eccentric driven fuel pumps, and diaphragm and spring-loaded fuel-injection valves. A diaphragm type maximum cylinder pressure indicator was used in part of these investigations with which the cylinder pressures were controlled to definite valves. The performance of the engines when equipped with each of the combustion chambers is discussed. The best performance for the tests reported was obtained with a bulb-type combustion chamber designed to give a high degree of turbulence within the bulb and cylinder. (author)
    Type: NACA-TR-282
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  • 48
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    The Effects of Fuel and Cylinder Gas Densities on the Characteristics of Fuel Sprays for Oil Engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted as a part of a general research on fuel-injection engines for aircraft. The purpose of the investigation was to determine the effects of fuel and cylinder gas densities with several characteristics of fuel sprays for oil engines. The start, growth, and cut-off of single fuel sprays produced by automatic injection valves were recorded on photographic film by means of special high-speed motion-picture apparatus. This equipment, which has been described in previous reports, is capable of taking twenty-five consecutive pictures of the moving spray at the rate of 4,000 per second. The penetrations of the fuel sprays increased and the cone angles and relative distributions decreased with increase in the specific gravity of the fuel. The density of the gas into which the fuel sprays were injected controlled their penetration. This was the only characteristic of the chamber gas that had a measurable effect upon the fuel sprays. Application of fuel-spray penetration data to the case of an engine, in which the pressure is rising during injection, indicated that fuel sprays may penetrate considerably farther than when injected into a gas at a density equal to that of the gas in an engine cylinder at top center.
    Type: NACA-TR-281
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  • 49
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    Lift, Drag, and Elevator Hinge Moments of Handley Page Control Surfaces (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report combines the wind tunnel results of tests on four control surface models made in the two wind tunnels of the Navy Aerodynamic Laboratory, Washington Navy Yard, during the years of 1922 and 1924, and submitted for publication to the National Advisory Committee for Aeronautics May 7, 1927. The purpose of the tests was to compare, first, the lifts and the aerodynamic efficiencies of the control surfaces from which their relative effectiveness as tail planes could be determined; then the elevator hinge moments upon which their relative ease of operation depended. The lift and drag forces on the control surface models were obtained for various stabilizer angles and elevator settings in the 8 by 8 foot tunnel by the writer in 1922; the corresponding hinge moments were found in the 4 by 4 foot tunnel by Mr. R. M. Bear in 1924. (author)
    Type: NACA-TR-278
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  • 50
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    The Effect of the Walls in Closed Type Wind Tunnels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of tests has been conducted during the period 1925-1927 by the National Advisory Committee for Aeronautics in the variable-density wind tunnel on several airfoil models of different sizes and sections to determine the effect of tunnel-wall interference and to determine a correction which can be applied to reduce the error caused thereby. The use of several empirical corrections was attempted with little success. The Prandtl theoretical corrections give the best results, and their use is recommended for correcting closed wind tunnel results to the conditions of free air. An appendix is attached wherein the experimentally determined effect of the walls on the tunnel velocity very close to their surface is given. This is of special interest because a "scale effect" was found in the boundary layer with a change in the density of the tunnel air.
    Type: NACA-TR-275
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  • 51
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    Structures of Thin Sheet Metal, Their Design and Construction (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a brief survey of the uses of sheet-metal coverings in conjunction with the inner structure. A method of construction is presented as well as a discussion on the strength of sheet metal.
    Type: NACA-TM-490
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  • 52
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    The comparative performance of an aviation engine at normal and high inlet air temperatures (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents some results obtained during an investigation to determine the effect of high inlet air temperature on the performance of a Liberty 12 aviation engine. The purpose of this investigation was to ascertain, for normal service carburetor adjustments and a fixed ignition advance, the relation between power and temperature for the range of carburetor air temperatures that may be encountered when supercharging to sea level pressure at altitudes of over 20,000 feet and without intercooling when using plain aviation gasoline and mixtures of benzol and gasoline. The results show that for the conditions of test, both the brake and indicated power decrease with increase in air temperature at a faster rate than given by the theoretical assumption that power varies inversely as the square root of the absolute temperature. On a brake basis, the order of the difference in power for a temperature difference of 120 degrees F. Is 3 to 5 per cent. The observed relation between power and temperature when using the 30-70 blend was found to be linear. But, although these differences are noted, the above theoretical assumption may be considered as generally applicable except where greater precision over a wide range of temperatures is desired, in which case it appears necessary to test the particular engine under the given conditions. (author)
    Type: NACA-TR-277
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  • 53
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    The N.A.C.A. Photographic Apparatus for Studying Fuel Sprays from Oil Engine Injection Valves and Test Results from Several Researches (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Apparatus for recording photographically the start, growth, and cut-off of oil sprays from injection valves has been developed at the Langley Memorial Aeronautical Laboratory. The apparatus consists of a high-tension transformer by means of which a bank of condensers is charged to a high voltage. The controlled discharge of these condensers in sequence, at a rate of several thousand per second, produces electric sparks of sufficient intensity to illuminate the moving spray for photographing. The sprays are injected from various types of valves into a chamber containing gases at pressures up to 600 pounds per square inch. Several series of pictures are shown. The results give the effects of injection pressure, chamber pressure, specific gravity of the fuel oil used, and injection-valve design, upon spray characteristics.
    Type: NACA-TR-274
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  • 54
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    The relative performance obtained with several methods of control of an overcompressed engine using gasoline (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents some results obtained during an investigation to determine the relative characteristics for several methods of control of an overcompressed engine using gasoline and operating under sea-level conditions. For this work, a special single cylinder test engine, 5-inch bore by 7-inch stroke, and designed for ready adjustment of compression ratio, valve timing and valve lift while running, was used. This engine has been fully described in NACA-TR-250. Tests were made at an engine speed of 1,400 R. P. M. for compression ratios ranging from 4.0 to 7.6. The air-fuel ratios were on the rich side of the chemically correct mixture and were approximately those giving maximum power. When using plain domestic gasoline, detonation was controlled to a constant, predetermined amount (audible), such as would be permissible for continuous operation, by (a) throttling the carburetor, (b) maintaining full throttle but greatly retarding the ignition, and (c) varying the timing of the inlet valve to reduce the effective compression ratio. From the results of the tests, it may be concluded that method (b) gives the best all-round performance and, being easily employed in service, appears to be the most practicable method for controlling an overcompressed engine using gasoline at low altitudes.
    Type: NACA-TR-272
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  • 55
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    Pressure Distribution Tests on PW-9 Wing Models Showing Effects of Biplane Interference (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report tests are described in which the distribution of pressures over models of the wings of the PW-9 Airplane was investigated. The wing models were tested individually and in the biplane combination. The investigation was conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. It is concluded in this paper that the effect of biplane interference on the pressures on the wings is practically confined to the lower surface of the upper wing and the upper surface of the lower wing; that the overhanging portion of the upper wing is not greatly affected by the presence of the lower wing; and that a slight washing at the center section of the upper wing satisfactorily compensates for a reduced chord at this section (providing the airfoil section is not mutilated) and prevents a large reduction in the normal force over this portion of the wing.
    Type: NACA-TR-271
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  • 56
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    A Full-Scale Investigation of Ground Effect (1928)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: This report describes flight tests which were made with the Vought VE-7 airplane to determine the effects of flying close to the ground. It is found that the drag of an airplane is materially reduced upon approaching the ground and that the reduction may be satisfactorily calculated according to theoretical formulas. Several aspects of ground effect which have had much discussion are explained.
    Type: NACA-TR-265
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  • 57
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    Drag of wings with end plates (1928)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: In this report a formula for calculating the induced drag of multiplanes with end plates is derived. The frictional drag of the end plates are used, is sufficiently large to increase the efficiency of the wing. Curves showing the reduction of drag for monoplanes and biplanes are constructed; the influence of gap-chord ratio, aspect ratio, and height of end plate are determined for typical cases. The method of obtaining the reduction of drag for a multiplane is described. Comparisons are made of calculated and experimental results obtained in wind tunnel tests with airfoils of various aspect ratios and end plates of various sizes. The agreement between calculated and experimental results is good. Analysis of the experimental results shows that the shape and section of the end plates are important.
    Type: NACA-TR-267
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  • 58
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    The Effect of a Flap and Ailerons on the N.A.C.A. M-6 Airfoil Section (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the results obtained at the Langley Memorial Aeronautical Laboratory on an N. A. C. A. M-6 airfoil, fitted with a flap and ailerons, and tested in the variable density wind tunnel at a density of 20 atmospheres. Airfoil characteristics are given for the model up to 48 degree angle of attack with the flap set at various angles, and also with the ailerons set at similar angles. The approximate lift distribution and the center of pressure variation along the span are determined with the model at 18 degree angle of attack and with the ailerons displaced at 20 degrees. Approximate rolling moment and yawing moment coefficients are determined for the various aileron settings. A comparison of the calculated angles of zero lift and the calculated lift and moment coefficiencies with those observed is given in the appendix.
    Type: NACA-TR-260
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  • 59
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    Combustion time in the engine cylinder and its effect on engine performance (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a general program to study combustion in the engine cylinder and to correlate the phenomena of combustion with the observed performance of actual engines, this paper presents a sketchy outline of what may happen in the engine cylinder during the burning of a charge. It also suggests the type of information needed to supply the details of the picture and points out how combustion time and rate affect the performance of the engine. A theoretical concept of a flame front which is assumed to advance radially from the point of ignition is presented, and calculations based on the area and velocity of this flame and the density of the unburned gases are made to determine the mass rate of combustion. From this rate the mass which has been burned and the pressure at any instant during combustion are computed. This process is then reversed in an effort to determine actual rates of combustion and flame velocities from the pressures as recorded on indicator diagrams. The effects of different rates of combustion on engine performance are then discussed and the importance of proper spark advance is emphasized.
    Type: NACA-TR-276
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  • 60
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    Wind Tunnel Tests on Autorotation and the "Flat Spin." (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with the autorotational characteristics of certain differing wing systems as determined from wind tunnel tests made at the Langley Memorial Aeronautical Laboratory. The investigation was confined to autorotation about a fixed axis in the plane of symmetry and parallel to the wind direction. Analysis of the tests leads to the following conclusions: autorotation below 30 degree angle of attack is governed chiefly by wing profile, and above that angle by wing arrangement. The strip method of autorotation analysis gives uncertain results between maximum C subscript L and 35 degrees. The polar curve of a wing system, and to a lower degree of accuracy the polar of a complete airplane model are sufficient for direct determination of the limits of rotary instability, subject to strip method limitations. The results of the investigation indicate that in free flight a monoplane is incapable of flat spinning, whereas an unstaggered biplane has inherent flat-spinning tendencies. The difficulty of maintaining equilibrium in stalled flight is due primarily to rotary instability, a rapid change from stability to instability occurring as the angle of maximum lift is exceeded. (author)
    Type: NACA-TR-273
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  • 61
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    Air Force Tests of Sperry Messenger Model with Six Sets of Wings (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this test was to compare six well-known airfoils, the R.A.F 15, U.S.A. 5, U.S.A. 27, U.S.A. 35-B, Clark Y, and Gottingen 387, fitted to the Sperry Messenger model, at full scale Reynolds number as obtained in the variable density wind tunnel of the National Advisory Committee for Aeronautics; and to determine the scale effect on the model equipped with all the details of the actual airplane. The results show a large decrease in minimum drag coefficient upon increasing the Reynolds number from about one-twentieth scale to full scale. Maximum lift coefficient was increased with increasing scale for all the airfoils except the Gottingen 387, for which it was slightly decreased. A comparison is made between the results of these tests and those obtained from tests made in this tunnel on airfoils alone. (author)
    Type: NACA-TR-269
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  • 62
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    Air force and moment for N-20 wing with certain cut-outs (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The airplane designer often finds it necessary, in meeting the requirements of visibility, to remove area or to otherwise locally distort the plan or section of an airplane wing. This report, prepared for the Bureau of Aeronautics January 15, 1925, contains the experimental results of tests on six 5 by 30 inch N-20 wing models, cut out or distorted in different ways, which were conducted in the 8 by 8 foot wind tunnel of the Navy Aerodynamical Laboratory in Washington in 1924. The measured and derived results are given without correction for vl/v for wall effect and for standard air density, p=0.00237 slug per cubic foot.
    Type: NACA-TR-266
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    Resistance and Cooling Power of Various Radiators (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This reports combines the wind tunnel results of radiator tests made at the Navy Aerodynamical Laboratory in Washington during the summers of 1921, 1925, and 1926. In all, 13 radiators of various types and capacities were given complete tests for figure of merit. Twelve of these were tested for resistance to water flow and a fourteenth radiator was tested for air resistance alone, its heat dissipating capacity being known. All the tests were conducted in the 8 by 8 foot tunnel, or in its 4 by 8 foot restriction, by the writer and under conditions as nearly the same as possible. That is to say, as far as possible, the general arrangement and condition of the apparatus, the observation intervals, the ratio of water flow per unit of cooling surface, the differential temperatures, and the air speeds were the same for all.
    Type: NACA-TR-261
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  • 64
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    Preliminary Flight Tests of the N.A.C.A. Roots Type Aircraft Engine Supercharger (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the suitability of the N.A.C.A. Roots type aircraft engine supercharger to flight-operating conditions, as determined the effects of the use of the supercharger upon engine operation and airplane performance, is described in this report. Attention was concentrated on the operation of the engine-supercharger unit and on the improvement of climbing ability; some information concerning high speeds at altitude was obtained. The supercharger was found to be satisfactory under flight-operating conditions. Although two failures occurred during the tests, the causes of both were minor and have been eliminated. Careful examination of the engines revealed no detrimental effects which could be attributed to supercharging. Marked improvements in climbing ability and high speeds at altitude were effected. It was also found that the load which could be carried to a given moderate or high altitude in a fixed time was considerably augmented. A slight sacrifice of low-altitude performance was necessitated, however, by the use of a fixed-pitch propeller. From a consideration of the very satisfactory flight performance of the Roots supercharger and of its inherent advantages, it is concluded that this type is particularly attractive for use in certain classes of commercial airplanes and in a number of military types.
    Type: NACA-TR-263
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  • 65
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    Annual report of the National Advisory Committee for Aeronautics (13th).administrative report including Technical Reports nos. 257 to 282 (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Type: NACA-AR-13
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  • 66
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    The Armstrong Whitworth "Starling" (British) : (single seat fighter) (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-82
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  • 67
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    On the take-off of heavily loaded airplanes (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report examines the take-off conditions of airplanes equipped with tractive propellers, and particularly the more difficult take-off of airplanes heavily loaded per unit of wing area (wing loading) or per unit of engine power (power loading).
    Type: NACA-TM-489
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  • 68
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    The constructional design of metal flying-boat hulls. Part I (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-487
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  • 69
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    Research on the control of airplanes (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Our task is to endeavor to obtain precise experimental records of the motion of stalled airplanes, both when left to themselves and when the pilot is trying to control them. The apparatus which we use consists of a box containing tree gyroscopes which are slightly deflected against a spring control when the airplane is turning.
    Type: NACA-TM-485
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  • 70
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    Tank Tests of Twin Seaplane Floats (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The following report contains the most essential data for the hydrodynamic portion of the twin-float problem. The following points were successfully investigated: 1) difference between stationary and nonstationary flow; 2) effect of the shape of the step; 3) effect of distance between floats; 4) effect of nose-heavy and tail-heavy moments; 5) effect of the shape of floats; 6) maneuverability.
    Type: NACA-TM-486
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  • 71
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    The cells of giant airplanes (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a discussion of the Rohrbach type of giant airplane. The problems considered are structural drag, wing loading and divided power plants.
    Type: NACA-TM-478
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  • 72
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    Airplane strength calculations and static tests in Russia : an attempt at standardization (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: We are here giving a summary of the rules established by the Theoretical Section of the Central Aerodynamic Institute of Moscow for the different calculation cases of an airplane. It appears the engineers of the Aerodynamic Institute considered only thick or medium profiles. For these profiles they have attempted to increase the safety when the center of pressure moves appreciably toward the trailing edge.
    Type: NACA-TM-480
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  • 73
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    Contribution to the design and calculation of fuel cams and fuel valves for diesel engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this work I have attempted to find a basis for the design of fuel cams, which will serve equally for large and small engines, both high-speed and low-speed.
    Type: NACA-TM-477
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  • 74
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    Synopsis of French Aeronautic Equipment : Aeronautic Instruments (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Different control instruments are discussed such as: air-speed indicators; angle-of-attack indicators; longitudinal inclinometers; turn indicators; stall indicators; and drift indicators.
    Type: NACA-TM-476
    Format: application/pdf
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  • 75
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    Recent researches on the air resistance of spheres (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The following conclusions on air resistance of spheres are drawn: 1) disturbances in front of the sphere and even single fine wires affect the critical Reynolds Number; 2) disturbances around the sphere increased the drag of the sphere without martially affecting the value of the Reynolds Number(sub crith); 3) great disturbances of the boundary layer of the sphere likewise change R.N.(sub crith); 4) turbulence of the approaching air stream lowers critical R.N.
    Type: NACA-TM-475
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  • 76
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    Windmills in the light of modern research (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The chief contribution of modern research in the field of windmills is a better understanding of the phenomena and of the available means for the accomplishment of certain results, but also of the natural limits to their productive capacity.
    Type: NACA-TM-474
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  • 77
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    The problem of noise in civil aircraft and the possibilities of its elimination (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The problem of noise in aircraft is considered and some solutions are presented.
    Type: NACA-TM-473
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  • 78
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    Technical Progress Shown in the 1927 Rhon Soaring-Flight Contest (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Since 1922 the further development of the glider has consisted of a very gradual and arduous improvement in regards to air resistance, weight, strength and maneuverability. This report provides an in-depth examination of these improvements.
    Type: NACA-TM-471
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  • 79
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    On improvement of air flow in wind tunnels (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The most important aerodynamical qualities that should be aimed at in wind tunnel design, are as follows: 1) constant and parallel direction of flow; 2) uniform velocity across all sections; 3) absence of turbulent motion; 4) constant velocity of flow. The above-mentioned qualities are all realized in a high degree in the Gottingen type of wind tunnel, with a parallel portion before the working section, the cross section of which is steadily reduced. It is shown in what follows, that the system can be applied to other wind tunnels, such as the N.P.L. or Eiffel type.
    Type: NACA-TM-470 , Society of Mechanical Engineers (108th : 1925).
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  • 80
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    Ignition and combustion phenomena in Diesel engines (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Evidences were found that neither gasification nor vaporization of the injected fuel occurs before ignition; also that the hydrogen coefficient has no significance. However the knowledge of the ignition point and of the "time lag" is important. After ignition, the combustion proceeds in a series of reactions, the last of which at least are now known.
    Type: NACA-TM-482
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  • 81
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    The Diesel as a Vehicle Engine (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The thorough investigation of a Dorner four-cylinder, four-stroke-cycle Diesel engine with mechanical injection led me to investigate more thoroughly the operation of the Diesel as a vehicle engine. Aside from the obvious need of reliability of functioning, a high rotative speed, light weight and economy in heat consumption per horsepower are also indispensable requirements.
    Type: NACA-TM-467
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  • 82
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    Wheel brakes and their application to aircraft (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advantages to be gained from braking have not been ignored, and in the search for a suitable method many schemes have been suggested and tried. Some of the methods discussed in this paper include: 1) increasing the height of the landing gear; 2) air brakes of various forms; 3) sprags on tail skid and axle; and 4) wheel brakes. This report focuses on the design of wheel brakes and wheel brake controls.
    Type: NACA-TM-466
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  • 83
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    Ignition points and combustion reactions in Diesel engines. Part II (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Ignition point measurement and ignition point test equipment is examined.
    Type: NACA-TM-484
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  • 84
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    Discussion of problems relating to the safety of aviation. Part II (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report focuses on structural strength and engine design in building and designing safer aircraft.
    Type: NACA-TM-465
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  • 85
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    Choice of profile for the wings of an airplane. Part II (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a general method for drawing airplane profiles. This method is useful, but it leads to a somewhat laborious drawing which becomes quite complicated when we take a transformation function having terms of a high degree.
    Type: NACA-TM-469
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  • 86
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    Discussion of problems relating to the safety of aviation. Part I (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The object of the present treatise is to examine the present status of aerial safety and to review the efforts of various commissions to promote safety.
    Type: NACA-TM-464
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  • 87
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    Ignition points and combustion reactions in Diesel engines. Part I (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The question of whether the fuel should be adapted to the engine or whether it is possible to improve equipment such as carburetors and engines so that as much of the crude oil as possible may be used without further transformation is examined in this report. Various ignition points and fuel mixtures are investigated in this regard.
    Type: NACA-TM-483
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  • 88
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    Choice of profile for the wings of an airplane. Part I (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The choice of the profile for the wings of an airplane is a problem which should be solved by a scientific method based on data obtained by systematic experimentation. The problem, in its present form, may be stated as follows: "To find a profile which has certain required aerodynamic characteristics and which encloses the spars, whose number, dimensions and separating distance are likewise determined by structural considerations." At present, the static test, corresponding to the case of accelerated flight at limited speed, requires the knowledge of the moment of the aerodynamic resultant at the angle of zero lift, and the possibility of controlling the magnitude of the corresponding absolute coefficient within more or less extensive limits.
    Type: NACA-TM-468
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  • 89
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    A few more mechanical-flight formulas without the aid of polar diagrams (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The reliability of the assumption of a parabolic shape of the polar curve is investigated and found satisfactory for all practical purposes. It is further shown that the aerodynamically best possible or "ideal" airplane is produced on this assumption. Lastly, detailed suggestions are given on the possibilities of application of this method of calculation. It especially simplifies the design and evaluation of structural changes and the determination of the limits of technical possibilities. The present report deals only with the relations of the airfoils. The mutual action of the airfoils, engine and propeller will be treated in a subsequent report.
    Type: NACA-TM-457
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  • 90
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    The 1926 German seaplane contest (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The report discusses the problem of rating the various seaplane designs from the 1926 seaplane contest. The whole process of rating consists in measuring the climbing speed, flying weight and carrying capacity of a seaplane and then using these data as the basis of a construction problem.
    Type: NACA-TM-454
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  • 91
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    Calculation of Airplane Performances Without the Aid of Polar Diagrams (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For good profiles the profile-drag coefficient is almost constant in the whole range which comes into consideration for practical flight. This is manifest in the consideration of the Gottingen airfoil tests and is confirmed by the investigations of the writer (measurements of the profile drag during flight by the Betz method), concerning which a detailed report will soon be published. The following deductions proceed from this fact. The formulas developed on the assumptions of a constant profile-drag coefficient afford an extensive insight into the influences exerted on flight performances by the structure of the airplane.
    Type: NACA-TM-456
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  • 92
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    Welding in airplane construction (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present article attempts to explain the principles for the production of a perfect weld and to throw light on the unexplained problems. Moreover, it is intended to elucidate the possibilities of testing the strength and reliability of welded parts.
    Type: NACA-TM-453
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  • 93
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    Influence of fuselage on propeller design (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present paper I shall not consider the problem of the best arrangement of airplane and propeller, but only a simple method for designing a propeller for a given arrangement of airplane parts. The inflow to the propeller and hence the efficiency of the propeller is affected most by the fuselage.
    Type: NACA-TM-492
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  • 94
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    Determination of the air forces and moments produced by the ailerons of an airplane (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distribution, so that an approximate evaluation of the distribution may be regarded as satisfactory. After a few brief remarks on the fundamentals of the exact computation, the method will be so presented that the lift distribution for deflected ailerons may be determined for other values of the parameter p from the results already obtained. Coefficients will then be given in the form of diagrams and numerical tables, from which the desired forces and moments can be easily obtained by substitution in the given equations.
    Type: NACA-TM-488
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  • 95
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    The span as a fundamental factor in airplane design (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Previous theoretical investigations of steady curvilinear flight did not afford a suitable criterion of "maneuverability," which is very important for judging combat, sport and stunt-flying airplanes. The idea of rolling ability, i.e., of the speed of rotation of the airplane about its X axis in rectilinear flight at constant speed and for a constant, suddenly produced deflection of the ailerons, is introduced and tested under simplified assumptions for the air-force distribution over the span. This leads to the following conclusions: the effect of the moment of inertia about the X axis is negligibly small, since the speed of rotation very quickly reaches a uniform value.
    Type: NACA-TM-479
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  • 96
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    Considerations on propeller efficiency (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The propeller cannot be considered alone, but the mutual interference between propeller and airplane must be considered. These difficulties are so great when the joint action of propeller and airplane is considered, that the aerodynamic laboratory at Gottingen originally abandoned the idea of applying the efficiency conception of the test results. These difficulties and the methods by which they are overcome are outlined in this report.
    Type: NACA-TM-481
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  • 97
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    Note on research work by Helmholtz and Wien relating to the form of waves propagated along the surface of separation of two liquids (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a clearer understanding of Helmholtz's work on the calculation of waves along the separation of two different liquids.
    Type: NACA-TM-455
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  • 98
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    Motion of fluids with very little viscosity (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: I have set myself the task to investigate systematically the laws of motion of a fluid whose viscosity is assumed to be very small. The viscosity is supposed to be so small that it can be disregarded wherever there are no great velocity differences nor accumulative effects.
    Type: NACA-TM-452
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  • 99
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    Experiments with a wing from which the boundary layer is removed by pressure or suction (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: With an unsymmetrical wing and a rotating Magnus cylinder, the lift is produced by the superposition of parallel and circulatory flows. An explanation of the circulatory flow is furnished by the boundary-layer theory of Prandtl and the consequent vortex formation. According to this explanation, it must evidently be possible to increase the circulation either by increasing the size of the stronger (lower) vortex or by decreasing the size of the weaker (upper) vortex. In this sense, according to Professor H. Zickendraht, we have a new type of wing from which the boundary layer is removed by forcing air out or sucking it in through openings in the upper surface of the wing near its trailing edge.
    Type: NACA-TM-472
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  • 100
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    Aviation fuels : with especial reference to "white spirit." (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Gasoline, the fuel now used, is an extremely volatile and inflammable liquid capable of forming explosive mixtures, the cause of many catastrophes in aviation. It is therefore of special interest to investigate the possibility of using fuels which, while being less volatile than gasoline, would nevertheless enable this engine to function satisfactorily.
    Type: NACA-TM-451
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