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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1934
 Collection: National Advisory Committee for Aeronautics Collection
The Aachen wind-tunnel balance

The Aachen wind-tunnel balance

Date: November 1934
Creator: Wieselsberger, C
Description: A description of the balance in the Aachen wind-tunnel.
Contributing Partner: UNT Libraries Government Documents Department
Additional test data on static longitudinal stability

Additional test data on static longitudinal stability

Date: August 1934
Creator: Hubner, Walter
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic analysis of the gyroplane rotating-wing system

The aerodynamic analysis of the gyroplane rotating-wing system

Date: March 1934
Creator: Wheatley, John B
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. Curves of lift-drag ratio against lift coefficient have been calculated for a typical case, showing the effect of varying the pitch angle, the solidarity, and the average blade-section drag coefficient. The analysis expresses satisfactorily the qualitative relations between the rotor characteristics and the rotor parameters. As disclosed by this investigation, the aerodynamic principles of the gyroplane are sound, and further research on this wing system is justified.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of anemometer cups

Aerodynamic characteristics of anemometer cups

Date: February 1934
Creator: Brevoort, M J & Joyner, U T
Description: The static lift and drag forces on three hemispherical and two conical cups were measured over a range of angles of attack from 0 degrees to 180 degrees and a range of Reynolds Numbers from very small up to 400,000. The problems of supporting the cup for measurement and the effect of turbulence were also studied. The results were compared with those of other investigators.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic effects of a split flap on the spinning characteristics of a monoplane model

Aerodynamic effects of a split flap on the spinning characteristics of a monoplane model

Date: December 1934
Creator: Bamber, M J
Description: 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 changes in coefficients produced by adding the split flaps are given for longitudinal force, normal force, and rolling and yawing moments about body axes. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to have much beneficial effect on a spin, and it might make the spin dangerous. The change in the spin will depend upon the aerodynamic and inertia characteristics of the particular airplane. A dangerous condition is most likely to be attained with airplanes which are statically stable in yaw in the spinning attitude and which have large weights distributed along wings.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Investigation of a Cup Anemometer

Aerodynamic Investigation of a Cup Anemometer

Date: July 1934
Creator: Hubbard, John D. & Brescoll, George P.
Description: Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic principles of the direct lifting propeller

Aerodynamic principles of the direct lifting propeller

Date: January 1934
Creator: Schrenk, Martin
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic rolling and yawing moments produced by floating wing-tip ailerons, as measured by spinning balance

Aerodynamic rolling and yawing moments produced by floating wing-tip ailerons, as measured by spinning balance

Date: March 1934
Creator: Bamber, Millard J
Description: 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. The tests were made with the spinning balance in the N.A.C.A. 5-foot vertical tunnel. The model was tested with and without the ailerons in 12 spinning attitudes chosen to cover the probable spinning range. Rolling- and yawing-moment coefficients are given as measured for the model with and without the ailerons, and computed values are given for the ailerons alone. The addition of floating wing-tip ailerons to the model doubled the rolling-moment coefficient and increased the yawing-moment coefficient by 0.05 and more. Both moments were in a sense to oppose the spin.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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.
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
Analysis of spinning in a monoplane wing by the induction method as compared with the strip method

Analysis of spinning in a monoplane wing by the induction method as compared with the strip method

Date: June 1, 1934
Creator: Poggi, L
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 induced velocities, which, however, are of such importance that their omission is bound to result in appreciable errors, as we attempt to prove in this report.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (19th).administrative report including Technical Report nos. 441 to 474

Annual report of the National Advisory Committee for Aeronautics (19th).administrative report including Technical Report nos. 441 to 474

Date: 1934
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
The Avia 51 commercial airplane (Czechoslovakian) : a cantilever high-wing monoplane

The Avia 51 commercial airplane (Czechoslovakian) : a cantilever high-wing monoplane

Date: February 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Avro 642 commercial airplane (British) : a high-wing cantilever monoplane

Avro 642 commercial airplane (British) : a high-wing cantilever monoplane

Date: May 1, 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Avro C.30 Direct-Control Autogiro (British)

Avro C.30 Direct-Control Autogiro (British)

Date: September 1, 1934
Creator: Colson, C N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Avro "Commodore" touring airplane (British) : a cabin biplane

The Avro "Commodore" touring airplane (British) : a cabin biplane

Date: July 1, 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The behavior under shearing stress of duralumin strip with round, flanged holes

The behavior under shearing stress of duralumin strip with round, flanged holes

Date: October 1, 1934
Creator: Schussler, Karl
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. Strips were clamped between two stationary end rails and one sliding center rail at which the shear is applied. The force was measured with a tension stirrup up to 20 tons and a compression dynamometer up to 10 tons. The displacement was recorded with the Zeiss dial gauge. The following were investigated: 1) effect of strip width; 2) strip thickness; 3) diameter of flanging; 4) depth of flanging; 5) and hole distance.
Contributing Partner: UNT Libraries Government Documents Department
The Bernard 82 military airplane (French) : a long-range monoplane

The Bernard 82 military airplane (French) : a long-range monoplane

Date: June 1, 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The British Klemm "Eagle" commercial airplane  : a low-wing cantilever monoplane

The British Klemm "Eagle" commercial airplane : a low-wing cantilever monoplane

Date: August 1, 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The calculated effect of trailing-edge flaps on the take-off of flying boats

The calculated effect of trailing-edge flaps on the take-off of flying boats

Date: November 1, 1934
Creator: Parkinson, J E & Bell, J W
Description: The results of take-off calculations are given for an application of simple trailing-edge flaps to two hypothetical flying boats, one having medium wing and power loading and consequently considerable excess of thrust over total resistance during the take-off run, the other having high wing and power loading and a very low excess thrust. For these seaplanes the effect of downward flap settings was: (1) to increase the total resistance below the stalling speed, (2) to decrease the get-away speed, (3) to improve the take-off performance of the seaplane having considerable excess thrust, and (4) to hinder the take-off of the seaplane having low excess thrust. It is indicated that flaps would allow a decrease in the high angles of wing setting necessary with most seaplanes, provided that the excess thrust is not too low.
Contributing Partner: UNT Libraries Government Documents Department
Calculation of horsepower available : appendix to estimation of the variation of thrust horsepower with air speed

Calculation of horsepower available : appendix to estimation of the variation of thrust horsepower with air speed

Date: July 1, 1934
Creator: Ober, Shatswell
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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