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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1936
 Collection: National Advisory Committee for Aeronautics Collection
The 5- by 7-meter wind tunnel of the DVL

The 5- by 7-meter wind tunnel of the DVL

Date: October 3, 1936
Creator: Kramer, M
Description: The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with Fowler flaps including flap loads, downwash, and calculated effect on take-off

Aerodynamic characteristics of a wing with Fowler flaps including flap loads, downwash, and calculated effect on take-off

Date: January 1, 1936
Creator: Platt, Robert C
Description: This report presents the results of wind tunnel tests of a wing in combination with each of three sizes of Fowler flap. The purpose of the investigation was to determine the aerodynamic characteristics as affected by flap chord and position, the air loads on the flaps, and the effect of flaps on the downwash.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of wings with cambered external airfoil flaps, including lateral control, with a full-span flap

Aerodynamic characteristics of wings with cambered external airfoil flaps, including lateral control, with a full-span flap

Date: January 1, 1936
Creator: Platt, Robert C
Description: The results of a wind-tunnel investigation of the NACA 23012, the NACA 23021, and the Clark Y airfoils, each equipped with a cambered external-airfoil flap, are presented in this report. The purpose of the research was to determine the relative merit of the various airfoils in combination with the cambered flap and to investigate the use of the flap as a combined lateral-control and high-lift device.
Contributing Partner: UNT Libraries Government Documents Department
Air flow in a separating laminar boundary layer

Air flow in a separating laminar boundary layer

Date: January 1, 1936
Creator: Schubauer, G. B.
Description: The speed distribution in a laminar boundary layer on the surface of an elliptic cylinder, of major and minor axes 11.78 and 3.98 inches, respectively, has been determined by means of a hot-wire anemometer. The direction of the impinging air stream was parallel to the major axis. Special attention was given to the region of separation and to the exact location of the point of separation. An approximate method, developed by K. Pohlhausen for computing the speed distribution, the thickness of the layer, and the point of separation, is described in detail; and speed-distribution curves calculated by this method are presented for comparison with experiment.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-pressure tables based on the United States standard atmosphere

Altitude-pressure tables based on the United States standard atmosphere

Date: January 1, 1936
Creator: Brombacher, W. G.
Description: This report is a revision of the altitude pressure tables of the United States standard atmosphere given in Technical Report No. 246. The altitude range has been extended from 50,000 to 80,000 feet.
Contributing Partner: UNT Libraries Government Documents Department
Analysis and model tests of autogiro jump take-off

Analysis and model tests of autogiro jump take-off

Date: October 1, 1936
Creator: Wheatley, John B & Bioletti, Carlton
Description: An analysis is made of the autogiro jump take-off, in which the kinetic energy of the rotor turning at excess speed is used to effect a vertical take-off. By the use of suitable approximations, the differential equation of motion of the rotor during this maneuver is reduced to a form that can be solved. Only the vertical jump was studied; the effect of a forward motion during the jump is discussed briefly. The results of model tests of the jump take-off have been incorporated in the paper and used to establish the relative accuracy of the results predicted from the analysis. Good agreement between calculation and experiment was obtained by making justifiable allowances.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of 2-spar cantilever wings with special reference to torsion and load transference

Analysis of 2-spar cantilever wings with special reference to torsion and load transference

Date: January 1, 1936
Creator: Kuhn, Paul
Description: This report deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined. The "Friedrichs-Von Karman equations" are shown to require the least amount of labor. Numerical examples by the several methods of analysis are given and the agreement between the calculation and experiment is shown.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of longitudinal stability in power-off flight with charts for use in design

An analysis of longitudinal stability in power-off flight with charts for use in design

Date: January 1, 1936
Creator: Zimmerman, Charles H
Description: This report presents a discussion of longitudinal stability in gliding flight together with a series of charts with which the stability characteristics of any airplane may be readily estimated.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of the three lowest bending frequencies of a rotating propeller

Analysis of the three lowest bending frequencies of a rotating propeller

Date: January 1, 1936
Creator: Liebers, F
Description: The available literature on rotating propeller oscillations reveals a lack of uniformity in interpretation, particularly as concerns the data on the overtone frequency with respect to the centrifugal forces. The present report is a survey of the existing data for computing the bending frequency and a check on the dependability of the calculating methods.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (21st).administrative report including Technical Report nos. 508 to 541

Annual report of the National Advisory Committee for Aeronautics (21st).administrative report including Technical Report nos. 508 to 541

Date: January 1, 1936
Creator: unknown
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.
Contributing Partner: UNT Libraries Government Documents Department
Automatic stabilization

Automatic stabilization

Date: December 1, 1936
Creator: Haus, FR
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Automatic stabilization

Automatic stabilization

Date: August 1, 1936
Creator: Haus, FR
Description: 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 feeding of Diesel engines by injection pumps actuated by engine compression, achieves the required high speeds of injection readily and permits rigorous control of the combustible charge introduced into each cylinder and of the peak pressure in the resultant cycle.
Contributing Partner: UNT Libraries Government Documents Department
The Avro "Anson" general-purpose airplane (British) : a two-engine low-wing cantilever monoplane

The Avro "Anson" general-purpose airplane (British) : a two-engine low-wing cantilever monoplane

Date: March 1, 1936
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Behavior of turbulent boundary layers on curved convex walls

Behavior of turbulent boundary layers on curved convex walls

Date: April 1, 1936
Creator: Schmidbauer, Hans
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Bending of beams of thin sections

Bending of beams of thin sections

Date: April 1, 1936
Creator: Huber, Maximilian T
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Boosted performance of a compression-ignition engine with a displaced piston

Boosted performance of a compression-ignition engine with a displaced piston

Date: May 1, 1936
Creator: Moore, Charles S & Foster, Hampton H
Description: Performance tests were made using a rectangular displacer arranged so that the combustion air was forced through equal passages at either end of the displacer into the vertical-disk combustion chamber of a single-cylinder, four-stroke-cycle compression-ignition test engine. After making tests to determine optimum displacer height, shape, and fuel-spray arrangement, engine-performance tests were made at 1,500 and 2,000 r.p.m. for a range of boost pressures from 0 to 20 inches of mercury and for maximum cylinder pressures up to 1,150 pounds per square inch. The engine operation for boosted conditions was very smooth, there being no combustion shock even at the highest maximum cylinder pressures. Indicated mean effective pressures of 240 pounds per square inch for fuel consumptions of 0.39 pound per horsepower-hour have been readily reproduced during routine testing at 2,000 r.p.m. at a boost pressure of 20 inches of mercury.
Contributing Partner: UNT Libraries Government Documents Department
Calculated effect of various types of flap on take-off over obstacles

Calculated effect of various types of flap on take-off over obstacles

Date: May 1, 1936
Creator: Wetmore, J W
Description: In order to determine whether or not flaps could be expected to have any beneficial effect on take-off performance, the distances required to take off and climb to an altitude of 50 feet were calculated for hypothetical airplanes, corresponding to relatively high-speed types and equipped with several types of flap. The types considered are the Fowler wing, the Hall wing, the split flap, the balanced split flap, the plain flap, and the external-airfoil flap. The results indicate that substantial reductions in take-off distance are possible through the use of flaps, provided that the proper flap angle corresponding to a given set of conditions is used. The best flap angle for taking off varies inversely as power loading and, to a much smaller extent, varies inversely with wing loading. Apparently, the best take-off characteristics are provided by the type of device in which the flap forms an extension to the main wing as in the case of the Fowler wing and the external-airfoil flap.
Contributing Partner: UNT Libraries Government Documents Department
Carbon-monoxide indicators for aircraft

Carbon-monoxide indicators for aircraft

Date: July 1, 1936
Creator: Womack, S H J & Peterson, J B
Description: Several improvements that have been made on commercially available carbon-monoxide indicators to make them more suitable for aircraft use are described. These improvements include an automatic flow regulator, which permits the use of a simplified instrument on aircraft where a source of suction is available, and a more reliable alarm attachment. A field method for testing instruments on standard samples of carbon monoxide is described. Performance data and instructions in operation and maintenance are given.
Contributing Partner: UNT Libraries Government Documents Department
The cetene scale and the induction period preceding the spontaneous ignition of diesel fuels in bombs

The cetene scale and the induction period preceding the spontaneous ignition of diesel fuels in bombs

Date: December 1, 1936
Creator: Michailova, M N & Neumann, M B
Description: In the present report a comparison is made between the scale obtained with mixtures of cetane and l-methyl naphthalene in a bomb, and that obtained with the same fuels in a Waukesha engine. The tests were conducted in a metal bomb heated by a Nichrome spiral. The fuel was injected into the bomb from a Bosch jet by means of a specially constructed plunger pump. The instant injection and the pressure curve in the bomb were registered by a beam of light which was reflected from a mirror connected to the needle of the jet and to a membrane indicator.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of the NACA 23012 airfoil from tests in the full-scale and variable-density tunnels

Characteristics of the NACA 23012 airfoil from tests in the full-scale and variable-density tunnels

Date: January 1, 1936
Creator: Jacobs, Eastman N & Clay, William C
Description: This report gives the results of tests in the NACA full-scale and variable-density tunnels of a new wing section, the NACA 23012, which is one of the more promising of an extended series of related airfoils recently developed. The tests were made at several values of the Reynolds number between 1,000,000 and 8,000,000. The new airfoil develops a reasonably high maximum lift and a low profile drag, which results in an unusually high value of the speed-range index. In addition, the pitching-moment coefficient is very small. The superiority of the new section over well-known and commonly used sections of small camber and moderate thickness is indicated by making a direct comparison with variable-density tests of the NACA 2212, the well-known NACA family airfoil that most nearly resembles it. The superiority is further indicated by comparing the characteristics with those obtained from full-scale-tunnel tests of the Clark y airfoil.
Contributing Partner: UNT Libraries Government Documents Department
Charts for calculating the performance of airplanes having constant-speed propellers

Charts for calculating the performance of airplanes having constant-speed propellers

Date: September 1, 1936
Creator: White, Roland J & Martin, Victor J
Description: Charts are presented for determining the performance of airplanes having variable-pitch propellers, the pitch of which is assumed to be adjusted to maintain constant speed for all rates of flight. The charts are based on the general performance equations developed by Oswald in reference 1, and are used in a similar manner. Examples applying the charts to airplanes having both supercharged and unsupercharged engines are included.
Contributing Partner: UNT Libraries Government Documents Department
Charts for checking the stability of compression members in trusses

Charts for checking the stability of compression members in trusses

Date: July 1, 1936
Creator: Borkmann, K
Description: The present report contains a set of charts developed for computing the fixity effect on a compression member in a truss through its adjacent members, the amount of fixity being considered variable with the particular total truss load. The use of the charts is illustrated on two- and three-bay systems, as well as on a triangular truss.
Contributing Partner: UNT Libraries Government Documents Department
Chief characteristics and advantages of tailless airplanes

Chief characteristics and advantages of tailless airplanes

Date: May 1, 1936
Creator: Dufaure De Lajarte, A
Description: This study will be concerned with the critical examination of two main questions, mainly, susceptibility of centering and more generally, the conditions of static stability, longitudinal equilibrium, and the question of dynamic stability, or at least the damping of longitudinal vibrations about a position of equilibrium that may result from a small variation in the angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
Circular motion of bodies of revolution

Circular motion of bodies of revolution

Date: February 1, 1936
Creator: Kaplan, Carl
Description: The circular motion for airship-like bodies has thus far been calculated only for a prolate ellipsoid of revolution (reference 1, p.133 and reference 2). In this paper, however, the circular motion of elongated bodies of revolution more nearly resembling airships will be investigated. The results will give the effect of rotation on the pressure distribution and thus yield some information as to the stresses set up in an airship in circular flight.
Contributing Partner: UNT Libraries Government Documents Department
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