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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
The aerodynamic forces and moments exerted on a spinning model of the NY-1 airplane as measured by the spinning balance

The aerodynamic forces and moments exerted on a spinning model of the NY-1 airplane as measured by the spinning balance

Date: January 1, 1934
Creator: Bamber, M J & Zimmerm, N, C h
Description: A preliminary investigation of the effects of changes in the elevator and rudder settings and of small changes in attitude upon the aerodynamic forces and moments exerted upon a spinning airplane was undertaken with the spinning balance in the 5-foot vertical tunnel of the National Advisory Committee for Aeronautics. The tests were made on a 1/12-scale model of the ny-1 airplane. Data by which to fix the attitude, the radius of spin, and the rotational and air velocities were taken from recorded spins of the full-scale airplane. Two spinning conditions were investigated. All six components of the aerodynamic reaction were measured and are presented in coefficient form refereed to airplane axes. The results indicate that the change in yawing moment produced by the rudder with the elevator up was the only component of force or moment produced by the elevator and rudder that could not have been balanced in an actual spin by small changes in attitude and angular velocity.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil section characteristics as affected by protuberances

Airfoil section characteristics as affected by protuberances

Date: January 1, 1934
Creator: Jacobs, Eastman N
Description: The drag and interference caused by protuberance from the surface of an airfoil have been determined in the NACA variable-density wind tunnel at a Reynolds number approximately 3,100,000. The effects of variations of the fore-and-aft position, height, and shape of the protuberance were measured by determining how the airfoil section characteristics were affected by the addition of the various protuberances extending along the entire span of the airfoil. The results provide fundamental data on which to base the prediction of the effects of actual short-span protuberances. The data may also be applied to the design of air brakes and spoilers.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of take-off run

The calculation of take-off run

Date: January 1, 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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
The estimation of maximum load capacity of seaplanes and flying boats

The estimation of maximum load capacity of seaplanes and flying boats

Date: January 1, 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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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