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Additional Test Data on Static Longitudinal Stability

Description: From Summary: "The purpose of this investigation was to explore the influence of weights of the controls on the stability with elevator released. The available test data were extended to stability with elevator locked. In this connection the study of the propeller effect seemed of vital importance."
Date: August 1934
Creator: HĂ¼bner, Walter
Partner: UNT Libraries Government Documents Department
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An Aerodynamic Analysis of the Autogiro Rotor With a Comparison Between Calculated and Experimental Results

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 ef… more
Date: January 17, 1934
Creator: Wheatley, John B.
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Analysis of the Gyroplane Rotating-Wing System

Description: "An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters" (p. 1).
Date: March 1934
Creator: Wheatley, John B.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Anemometer Cups

Description: From Introduction: "The investigation was intended to cover the characteristics of individual cups and of similar cups mounted on complete cup wheals. This report treats the static tests run on the individual cups."
Date: February 1934
Creator: Brevoort, M. J. & Joyner, U. T.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Effects of a Split Flap on the Spinning Characteristics of a Monoplane Model

Description: From Summary: "The investigation described in this report was made to determine the change in aerodynamic forces and moments produced by split flaps in a steady spin. The test were made with the spinning balance in the NACA 5-foot vertical wind tunnel. A low-wing monoplane model was tested with and without the split flaps in 12 spinning attitudes chosen to cover the probable spinning range. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to hav… more
Date: December 1934
Creator: Bamber, M. J.
Partner: UNT Libraries Government Documents Department
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The aerodynamic effects of wing cut-outs

Description: From Introduction: "The information now available concerning wing cut-outs or applicable to the analysis of their effects is plentiful (references 1 to 7) but too disconnected and unorganized to be of the greatest possible usefulness. In connection with the interference program being conducted in the N.A.C.A. varible-density wind tunnel, an analysis was therefore made of existing material to determine the qualitative effects of the different features of wing cut-outs, and to obtain means of cal… more
Date: 1934
Creator: Sherman, Albert
Partner: UNT Libraries Government Documents Department
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Aerodynamic principles of the direct lifting propeller

Description: From Summary: "The purpose of this report is to make the complicated processes on the direct-lift propeller amenable to analysis and observation. This is accomplished by placing the physical phenomena, starting with the most elementary process, in the foreground, while limiting the mathematical treatment to the most essential in view of the fundamental defects of the theorems. Comparison with model experiments supplements and corroborates the theoretical results."
Date: January 1934
Creator: Schrenk, Martin
Partner: UNT Libraries Government Documents Department
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Aerodynamic Rolling and Yawing Moments Produced by Floating Wing-Tip Ailerons, as Measured by Spinning Balance

Description: From Summary: "The investigation described in this report was made to determine the effectiveness of floating wing-tip ailerons as an airplane control in the spin. In these tests the ailerons, not being balanced, were set parallel to the axis of rotation, which is probably very nearly the attitude that balanced floating ailerons would assume in a spin. Rolling - and yawing moment coefficients are given as measured for the model with and without the ailerons, and computed values are given for th… more
Date: March 1934
Creator: Bamber, Millard J.
Partner: UNT Libraries Government Documents Department
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Air conditions close to the ground and the effect on airplane landings

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.
Date: April 3, 1934
Creator: Thompson, F. L.; Peck, W. C. & Beard, A. P.
Partner: UNT Libraries Government Documents Department
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Air flow in a separating laminar boundary layer

Description: Report discussing 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, th… more
Date: December 1, 1934
Creator: Schubauer, G. B.
Partner: UNT Libraries Government Documents Department
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Analysis of 2-Spar Cantilever Wings With Special Reference to Torsion and Load Transference

Description: "This paper 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" (p. 45).
Date: April 10, 1934
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department
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An Analysis of Longitudinal Stability in Power-Off Flight With Charts for Use in Design

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. The relationships governing stability characteristics are derived from equations of equilibrium referred to moving axes that are tangent and perpendicular to the instantaneous flight path. It is shown that instability of the motion can arise only through an increase of linear and angular momentum in the… more
Date: December 13, 1934
Creator: Zimmerman, Charles H.
Partner: UNT Libraries Government Documents Department
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Analysis of Spinning in a Monoplane Wing by the Induction Method as Compared With the Strip Method

Description: The problem of autorotation has been attacked by various authors, in particular Fuchs and Schmidt who applied the so-called strip method which is based upon the assumption that the forces and moments per unit length acting in each section of the wing are equal to those on an infinite cylindrical wing of equal section in an air flow of intensity and direction resulting from the apparent relative motion of this section with respect to the surrounding air. In other words they disregarded the induc… more
Date: June 1934
Creator: Poggi, L.
Partner: UNT Libraries Government Documents Department
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Annual Report of the National Advisory Committee for Aeronautics (19th). Administrative Report Including Technical Report Nos. 441 to 474

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.
Date: 1934
Partner: UNT Libraries Government Documents Department
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Applied Methods and Equipment for Reducing Evaporation Losses of Petroleum and Gasoline

Description: From Scope of Report: "The subject matter in this bulletin is divided as follows: Theory of evaporation; methods of determining evaporation losses; lease operation; transportation and storage of crude petroleum; and evaporation losses of gasoline at the refineries."
Date: 1934
Creator: Schmidt, Ludwig
Partner: UNT Libraries Government Documents Department
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The Avia 51 Commercial Airplane (Czechoslovakian): A Cantilever High-Wing Monoplane

Description: Circular describing the Avia 51 commercial airplane, which is a Czechoslovakian cantilever high-wing monoplane with a fairly orthodox design. Details of the performance, construction, wing, ailerons, fuselage, landing gear, engines, characteristics, drawings, and photographs are provided.
Date: February 1934
Partner: UNT Libraries Government Documents Department
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Avro C.30 Direct-Control Autogiro (British)

Description: Circular describing the Avro C.30 direct-control autogiro. Details of the construction, fuselage, engine mounting, tail, cockpits, rotor system, characteristics, performance, drawings, and photographs are provided.
Date: September 1934
Creator: Colson, C. N.
Partner: UNT Libraries Government Documents Department
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The Behavior Under Shearing Stress of Duralumin Strip With Round, Flanged Holes

Description: "This report presents the results of an investigation to determine the behavior of dural strip with flanged holes in the center when subjected to shear stresses. They buckle under a certain load just as a flat sheet. There is one optimum hole spacing and a corresponding buckling load in shear for each sheet width, sheet thickness, and flange form. Comparison with non-flanged sheets revealed a marked increase of buckling load in shear due to the flanging and a slightly greater displacement" (p. … more
Date: October 1934
Creator: SchĂ¼ssler, Karl
Partner: UNT Libraries Government Documents Department
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