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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1934
 Serial/Series Title: NACA Technical Reports
 Collection: Technical Report Archive and Image Library
An aerodynamic analysis of the autogiro rotor with a comparison between calculated and experimental results

An aerodynamic analysis of the autogiro rotor with a comparison between calculated and experimental results

Date: 1934
Creator: Wheatley, John B
Description: This report presents an extension of the autogiro theory of Glauert and Lock in which the influence of a pitch varying with the blade radius is evaluated and methods of approximating the effect of blade tip losses and the influence of reversed velocities on the retreating blades are developed. A comparison of calculated and experimental results showed that most of the rotor characteristics could be calculated with reasonable accuracy, and that the type of induced flow assumed has a secondary effect upon the net rotor forces, although the flapping motion is influenced appreciably. An approximate evaluation of the effect of parasite drag on the rotor blades established the importance of including this factor in the analysis.
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The aerodynamic effects of wing cut-outs

The aerodynamic effects of wing cut-outs

Date: 1934
Creator: Sherman, Albert
Description: In connection with the interference program being conducted in the NACA variable-density wind tunnel, an analysis was made of available material with the object of presenting a qualitative discussion on wing characteristics as affected by cut-outs and of determining means for their quantitative calculation.
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Air conditions close to the ground and the effect on airplane landings

Air conditions close to the ground and the effect on airplane landings

Date: April 3, 1934
Creator: Thompson, F L; Peck, W C & Beard, A P
Description: This report presents the results of an investigation undertaken to determine the feasibility of making glide landings in gusty air. Wind velocities were measured at several stations between the ground and a height of 51 feet, and flight tests were made to determine the actual influence of gusts on an airplane gliding close to the ground.
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Air flow in a separating laminar boundary layer

Air flow in a separating laminar boundary layer

Date: December 1, 1934
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.
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Aircraft power-plant instruments

Aircraft power-plant instruments

Date: January 1, 1934
Creator: Sontag, Harcourt & Brombacher, W. G.
Description: This report supersedes NACA-TR-129 which is now obsolete. Aircraft power-plant instruments include tachometers, engine thermometers, pressure gages, fuel-quantity gages, fuel flow meters and indicators, and manifold pressure gages. The report includes a description of the commonly used types and some others, the underlying principle utilized in the design, and some design data. The inherent errors of the instrument, the methods of making laboratory tests, descriptions of the test apparatus, and data in considerable detail in the performance of commonly used instruments are presented. Standard instruments and, in cases where it appears to be of interest, those used as secondary standards are described. A bibliography of important articles is included.
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The calculation of take-off run

The calculation of take-off run

Date: January 1934
Creator: Diehl, Walter S.
Description: A comparatively simple method of calculating length of take-off run is developed from the assumption of a linear variation in net accelerating force with air speed and it is shown that the error involved is negligible.
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A comparison between the theoretical and measured longitudinal stability characteristics of an airplane

A comparison between the theoretical and measured longitudinal stability characteristics of an airplane

Date: January 1, 1934
Creator: Soule, Hartley A & Wheatley, John B
Description: This report covers an investigation of the application of the theory of dynamic longitudinal stability, based on the assumption of small oscillations, to oscillations an airplane is likely to undergo in flight. The investigation was conducted with a small parasol monoplane for the fixed-stick condition. The period and damping of longitudinal oscillations were determined by direct measurements of oscillations in flight and also by calculation in which the factors that enter the theoretical stability equation were determined in flight. A comparison of the above-mentioned characteristics obtained by these two methods indicates that the theory is applicable to the conditions encountered in flight.
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Determination of the theoretical pressure distribution for twenty airfoils

Determination of the theoretical pressure distribution for twenty airfoils

Date: January 1, 1934
Creator: Garrick, I E
Description: This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons with experiment are indicated. The results presented may be of value in predicting structural loads and also in a correlation of theoretical pressure gradients with profile resistance.
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The drag of two streamline bodies as affected by protuberances and appendages

The drag of two streamline bodies as affected by protuberances and appendages

Date: January 1, 1934
Creator: Abbott, Ira H
Description: This report presents the results of wind tunnel tests of two airship models conducted to determine the drag coefficients at zero pitch, and the effect of fins and cars and of flat and streamlined protuberances located at various positions along the hull. During the investigation the stern of one model was rounded off to produce a blunter shape. The extreme range of the Reynolds number based on the over-all length of the models was from 1,300,000 to 33,000,000. At large values of the Reynolds number the streamlined protuberance affected the drag very little, and the additional drag caused by the flat protuberance was less than the calculated drag by the protuberance alone. The fins and cars together increased the bare-hull drag about 20 per cent.
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The estimation of maximum load capacity of seaplanes and flying boats

The estimation of maximum load capacity of seaplanes and flying boats

Date: January 1934
Creator: Diehl, Walter S.
Description: This reports presents a method of calculating time and gross load for take-off of seaplanes and flying boats.
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The experimental determination of the moments of inertia of airplanes

The experimental determination of the moments of inertia of airplanes

Date: January 1, 1934
Creator: Soule, Hartley A & Miller, Marvel P
Description: The application of the pendulum method to the experimental determination of the moments of inertia of airplanes is discussed in this report. Particular reference is made to the effects of the air, in which the airplane is immersed, on the swinging tests and to the procedure by which these effects are taken into account. This procedure has been used for some time, and the data on several airplanes for which the moments of inertia have been found are included.
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A flight investigation of the spinning of the NY-1 airplane with varied mass distribution and other modifications, and an analysis based on wind-tunnel tests

A flight investigation of the spinning of the NY-1 airplane with varied mass distribution and other modifications, and an analysis based on wind-tunnel tests

Date: January 1, 1934
Creator: Scudder, Nathan F
Description: This report presents the results of an investigation of the spinning characteristics of NY-1 naval training biplane. The results of flight tests and an analysis based on wind-tunnel test data are given and compared. The primary purpose of the investigation was the determination in flight of the effect of changes in mass distribution along the longitudinal axis, without change of mass quantity or centroid. Other effects were also investigated, such as those due to wing loading, center-of-gravity position, dihedral of wings, control setting, and the removal of a large portion of the fabric from the fin and rudder. The wind tunnel test results used in the numerical analysis were obtained in the 7 by 10 foot wind tunnel through an angle-of-attack.
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General Potential Theory of Arbitrary Wing Section

General Potential Theory of Arbitrary Wing Section

Date: January 1, 1934
Creator: Theodorsen, T & Garrick, I E
Description: This report gives the exact treatment of the problem of determining the 2-dimensional potential flow around wing sections of any type. The treatment is based directly on the solution of this problem as advanced by Theodorsen in NACA-TR-411. The problem condenses into the compact form of an integral equation capable of yielding numerical solutions by a direct process.
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Improved apparatus for the measurement of fluctuations of air speed in turbulent flow

Improved apparatus for the measurement of fluctuations of air speed in turbulent flow

Date: January 1, 1934
Creator: Mock, W C , Jr & Dryden, H L
Description: This report describes recent improvements in the design of the equipment associated with the hot-wire anemometer for the measurement of fluctuating air speeds in turbulent air flow, and presents the results of some experimental investigations dealing with the response of the hot wire to speed fluctuations of various frequencies. Attempts at measuring the frequency of the fluctuations encountered in the Bureau of Standards' 54-inch wind tunnel are also reported. In addition, the difficulties encountered in the use of such apparatus and the precautions found helpful in avoiding them are discussed.
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Increasing the air charge and scavenging the clearance volume of a compression-ignition engine

Increasing the air charge and scavenging the clearance volume of a compression-ignition engine

Date: January 1, 1934
Creator: Spanogle, J A; Hicks, C W & Foster, H H
Description: The object of the investigation presented in this report was to determine the effects of increasing the air charge and scavenging the clearance volume of a 4-stroke-cycle compression-ignition engine having a vertical-disk form combustion chamber. Boosting the inlet-air pressure with normal valve timing increased the indicated engine power in proportion to the additional air inducted and resulted in smoother engine operation with less combustion shock. Scavenging the clearance volume by using a valve overlap of 145 degrees and an inlet-air boost pressure of approximately 2 1/2 inches of mercury produced a net increase in performance for clear exhaust operation of 33 percent over that obtained with normal valve timing and the same boost pressure. The improved combustion characteristics result in lower specific fuel consumption, and a clearer exhaust.
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The interference between struts in various combinations

The interference between struts in various combinations

Date: January 1, 1934
Creator: Biermann, David & Herrnstein, William H , Jr
Description: This report presents the results of wind tunnel tests made to determine the interference drag arising from various arrangements of streamline struts and round struts, or cylinders. Determinations were made of the interference drag of struts spaced side by side, struts in tandem, tandem struts encased in a single fairing, a strut intersecting a plane, and struts intersecting to form a v. Three sizes of struts were used for most of the tests. These tests show that the interference drag arising from struts in close proximity may be of considerable magnitude, in some instances amounting to more than the drag of the struts themselves.
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Interference on an airfoil of finite span in an open wind tunnel

Interference on an airfoil of finite span in an open wind tunnel

Date: January 1, 1934
Creator: Theodorsen, Theodore
Description: The wall interference on an airfoil of finite span in an open-throat rectangular section has been treated theoretically and the result is presented in a convenient formula. Numerical results are given in tables and diagrams.
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Maneuverability investigation of an O3U-1 observation airplane

Maneuverability investigation of an O3U-1 observation airplane

Date: January 1934
Creator: Thompson, F. L. & Kirschbaum, H. W.
Description: This report presents the results of maneuverability tests of an O3U-1 observation airplane. This investigation is the third in a series of similar investigations requested by the Bureau of Aeronautics (Navy) for the purpose of comparing the maneuverability of different airplane types and to provide quantitative data for use in establishing a criterion or method for rating the maneuverability of an airplane. The two former investigations were conducted with the fighter types designated F6C-3 and F6C-4 and have been reported previously. Measurement of the air speed, the angular velocity, the linear acceleration, and positions of the controls were made during abrupt single-control maneuvers with three stop positions for each control, during steady horizontal turns for the determination of minimum radius, and during 180 degree turns by various methods. Flight-path coordinates in two dimensions were determined for the 180 degree turns by means of a special camera obscura designed for the previous investigation of the F6C-4 airplane. All maneuvers were performed at an altitude of approximately 3,000 feet.
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The NACA full-scale wind tunnel

The NACA full-scale wind tunnel

Date: January 1, 1934
Creator: Defrance, Smith J
Description: This report gives a complete description of the full-scale wind tunnel of the National Advisory Committee for Aeronautics.
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The NACA high-speed wind tunnel and tests of six propeller sections

The NACA high-speed wind tunnel and tests of six propeller sections

Date: January 1, 1934
Creator: Stack, John
Description: This report gives a description of the high-speed wind tunnel of the National Advisory Committee for Aeronautics. The operation of the tunnel is also described and the method of presenting the data is given. An account of an investigation of the aerodynamic properties of six propeller sections is included.
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The NACA tank : a high-speed towing basin for testing models of seaplane floats

The NACA tank : a high-speed towing basin for testing models of seaplane floats

Date: January 1, 1934
Creator: Truscott, Starr
Description: This report describes the high-speed model towing basin of the National Advisory Committee for Aeronautics, usually referred to as the NACA Tank. The purpose of this piece of equipment is to enable the Committee to provide information and data regarding the performance of seaplanes on the water analogous to the information furnished concerning the performance of airplanes in the air.
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Negative thrust and torque characteristics of an adjustable-pitch metal propeller

Negative thrust and torque characteristics of an adjustable-pitch metal propeller

Date: January 1, 1934
Creator: Hartman, Edwin P
Description: This report presents the results of a series of negative thrust and torque measurements made with a 4 foot diameter model of a conventional aluminum-alloy propeller. The tests were made in the 20-foot propeller-research tunnel of the National Advisory Committee for Aeronautics. The results show that the negative thrust is considerably affected by the shape and size of the body behind the propeller, that the maximum negative thrust increases with decrease in blade-angle setting, and that the drag of a locked propeller may be greatly reduced by feathering it into the wind. Several examples of possible applications of the data are given.
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On the theory of laminar boundary layers involving separation

On the theory of laminar boundary layers involving separation

Date: January 1, 1934
Creator: Von Karman, TH & Millikan, C
Description: This paper presents a mathematical discussion of the laminar boundary layer, which was developed with a view of facilitating the investigation of those boundary layers in particular for which the phenomenon of separation occurs. The treatment starts with a slight modification of the form of the boundary layer equation first published by Von Mises. Two approximate solutions of this equation are found, one of which is exact at the outer edge of the boundary layer while the other is exact at the wall. The final solution is obtained by joining these two solutions at the inflection points of the velocity profiles. The final solution is given in terms of a series of universal functions for a fairly broad class of potential velocity distributions outside of the boundary layer. Detailed calculations of the boundary layer characteristics are worked out for the case in which the potential velocity is a linear function of the distance from the upstream stagnation point. Finally, the complete separation point characteristics are determined for the boundary layer associated with a potential velocity distribution made up of two linear functions of the distance from the stagnation point. It appears that extensions of the detailed calculations to more complex ...
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Penetration and duration of fuel sprays from a pump injection system

Penetration and duration of fuel sprays from a pump injection system

Date: January 1, 1934
Creator: Rothrock, A M & Marsh, E T
Description: High-speed motion pictures were taken of individual fuel sprays from a pump injection system. The changes in the spray-tip penetration with changes in the pump speed, injection-valve opening and closing pressures, discharge-orifice area, injection-tube length and diameter, and pump throttle setting were measured. The pump was used with and without a check valve. The results show that the penetration of the spray tip can be controlled by the dimensions of the injection tube, the area of the discharge orifice, and the injection-valve opening and closing pressures.
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