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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1933
 Collection: Technical Report Archive and Image Library
The 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics

The 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics

Date: 1933
Creator: Harris, Thomas A
Description: This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
Contributing Partner: UNT Libraries Government Documents Department
The 1933 contest for the Deutsch de la Meurthe trophy

The 1933 contest for the Deutsch de la Meurthe trophy

Date: October 1933
Creator: Leglise, Pierre; Hirschauer, L & Saladin, Raymond
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of airfoils as affected by surface roughness

The aerodynamic characteristics of airfoils as affected by surface roughness

Date: April 1933
Creator: HOCKER RAY W
Description: The effect on airfoil characteristics of surface roughness of varying degrees and types at different locations on an airfoil was investigated at high values of the Reynolds number in a variable density wind tunnel. Tests were made on a number of National Advisory Committee for Aeronautics (NACA) 0012 airfoil models on which the nature of the surface was varied from a rough to a very smooth finish. The effect on the airfoil characteristics of varying the location of a rough area in the region of the leading edge was also investigated. Airfoils with surfaces simulating lap joints were also tested. Measurable adverse effects were found to be caused by small irregularities in airfoil surfaces which might ordinarily be overlooked. The flow is sensitive to small irregularities of approximately 0.0002c in depth near the leading edge. The tests made on the surfaces simulating lap joints indicated that such surfaces cause small adverse effects. Additional data from earlier tests of another symmetrical airfoil are also included to indicate the variation of the maximum lift coefficient with the Reynolds number for an airfoil with a polished surface and with a very rough one.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic effect of a retractable landing gear

The aerodynamic effect of a retractable landing gear

Date: March 1933
Creator: Defrance, Smith J
Description: Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels were extended reduced the drag only 2 percent at a lift coefficient of 1.0, which was assumed for the take-off condition. Therefore, the wheel openings in the bottom side of the wing have a negligible effect upon the take-off of the airplane. Retracting the landing gear reduced the minimum drag of the complete airplane 50 percent.
Contributing Partner: UNT Libraries Government Documents Department
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: February 7, 1933
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
Aerodynamic forces and moments of a seaplane on the water

Aerodynamic forces and moments of a seaplane on the water

Date: November 1933
Creator: Kohler, M
Description: This report gives the results of wind-tunnel tests with a seaplane model as a contribution to the solution of the aerodynamic problems. In the tests it was assumed that the seaplane rested motionless on the water and was exposed, in various positions with respect to the supposedly flat surface of the water, to a uniform air current 0 to 360 degrees.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes

Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes

Date: November 1933
Creator: Sanders, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes

Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes

Date: June 1933
Creator: Weick, Fred E & Sanders, Robert
Description: Wind tunnel tests were made of a model wing having an aspect ratio of 3 and a tapered plan form with a straight trailing edge. The model had the Clark Y airfoil section throughout it's entire span and had no washout, depending on a trailing-edge flap for longitudinal balance and control. The flap had a constant chord and was divided into four equal portions along the span. The tests were made with the entire flap deflected to obtain longitudinal control and balance, and also with the inner portions deflected alone, and with the outer portions deflected alone. It was found that the simple wing with no washout or change of basic section along the span has aerodynamic characteristics well suited for use on tailless airplanes. A higher lift coefficient was obtained with the full-span flap deflected as a unit to give longitudinal balance than was obtained with either the inner or the outer portions of the flap deflected.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft speed instruments

Aircraft speed instruments

Date: January 1, 1933
Creator: Beij, K Hilding
Description: This report presents a concise survey of the measurement of air speed and ground speed on board aircraft. Special attention is paid to the pitot-static air-speed meter which is the standard in the United States for airplanes. Air-speed meters of the rotating vane type are also discussed in considerable detail on account of their value as flight test instruments and as service instruments for airships. Methods of ground-speed measurement are treated briefly, with reference to the more important instruments. A bibliography on air-speed measurement concludes the report.
Contributing Partner: UNT Libraries Government Documents Department
An airfoil spanning an open jet

An airfoil spanning an open jet

Date: September 1933
Creator: Stuper, J
Description: Proceeding from the fundamental problem on the mutual relation of a wing and free boundaries the distribution of the circulation is determined for an airfoil spanning an open jet of rectangular section at different aspect ratios, and then for an open jet of circular section. The solution is obtained by means of a Fourier series and computations have been performed for different values of the variables. The second part describes the experiments performed for the purpose of proving the theory. The results confirm the theory. In conclusion it defines the induced drag of a wing extending across an open jet and compares it with the drag of a monoplane having a span equal to the jet width at equal total lift.
Contributing Partner: UNT Libraries Government Documents Department
The Airspeed "Courier" commercial airplane (British) : a low-wing cantilever monoplane

The Airspeed "Courier" commercial airplane (British) : a low-wing cantilever monoplane

Date: May 1933
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (18th).administrative report including Technical Report nos. 401 to 440

Annual report of the National Advisory Committee for Aeronautics (18th).administrative report including Technical Report nos. 401 to 440

Date: 1933
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
Application of practical hydrodynamics to airship design

Application of practical hydrodynamics to airship design

Date: January 1, 1933
Creator: Upson, Ralph H & Klikoff, W A
Description: The purpose of the first two parts of this report is to present in concise format all the formulas required for computation of the hydrodynamic forces, so that they can be easily computed for either straight or curvilinear flight. Improved approximations are also introduced having a high degree of accuracy throughout the entire range of practical proportions. The remaining two parts of the report are devoted respectively to stability and skin friction, as functions of the same hydrodynamic forces.
Contributing Partner: UNT Libraries Government Documents Department
Attaining a steady air stream in wind tunnels

Attaining a steady air stream in wind tunnels

Date: October 1933
Creator: Prandtl, L
Description: Many experimental arrangements of varying kind involve the problems of assuring a large, steady air stream both as to volume and to time. For this reason a separate discussion of the methods by which this is achieved should prove of particular interest. Motors and blades receive special attention and a review of existent wind tunnels is also provided.
Contributing Partner: UNT Libraries Government Documents Department
Behavior of Vortex Systems

Behavior of Vortex Systems

Date: June 1, 1933
Creator: Betz, A
Description: Progressive application of the Kutta-Joukowsky theorem to the relationship between airfoil lift and circulation affords a number of formulas concerning the conduct of vortex systems. The application of this line of reasoning to several problems of airfoil theory yields an insight into many hitherto little observed relations. This report is confined to plane flow, hence all vortex filaments are straight and mutually parallel (perpendicular to the plane of flow).
Contributing Partner: UNT Libraries Government Documents Department
The Caudron P.V. 200 touring airplane (French) : an all-metal amphibian monoplane

The Caudron P.V. 200 touring airplane (French) : an all-metal amphibian monoplane

Date: April 1, 1933
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel

The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel

Date: January 1, 1933
Creator: Jacobs, Eastman N; Ward, Kenneth E & Pinkerton, Robert M
Description: An investigation of a large group of related airfoils was made in the NACA variable-density wind tunnel at a large value of the Reynolds number. The tests were made to provide data that may be directly employed for a rational choice of the most suitable airfoil section for a given application. The variation of the aerodynamic characteristics with variations in thickness and mean-line form were systematically studied. (author).
Contributing Partner: UNT Libraries Government Documents Department
The characteristics of a Clark y wing model equipped with several forms of low-drag fixed slots

The characteristics of a Clark y wing model equipped with several forms of low-drag fixed slots

Date: January 1, 1933
Creator: Weick, Fred E & Wenzinger, Carl J
Description: This investigation was undertaken to develop a low-drag fixed slot for an airplane wing which would avoid the complications and maintenance difficulties of the present movable-type Handley Page slot. Tests were conducted on a series of fixed slots in an attempt to reduce the minimum drag coefficient without decreasing the maximum lift coefficient or the stalling angle of the slotted wing. The tests were made in the NACA 5-foot vertical wind tunnel on a Clark Y basic section having a 10-inch chord.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of Clark Y airfoils of small aspect ratios

Characteristics of Clark Y airfoils of small aspect ratios

Date: January 1, 1933
Creator: Zimmerman, C H
Description: This report presents the results of a series of wind tunnel tests showing the force, moment, and autorotational characteristics of Clark Y airfoils having aspect ratios varying from 0.5 to 3. An airfoil of rectangular plan form was tested with rectangular tips, flared tips, and semicircular tips. Tests were also made on one airfoil of circular plan form and two airfoils of elliptical plan form. The tests revealed a marked delay of the stall and a decided increase in values of maximum lift coefficient and maximum resultant force coefficient for aspect ratios of the order of 1 as compared with values for aspect ratios of 2 and 3.
Contributing Partner: UNT Libraries Government Documents Department
Charts for determining the pitching moment of tapered wings with sweepback and twist

Charts for determining the pitching moment of tapered wings with sweepback and twist

Date: December 1, 1933
Creator: Anderson, Raymond F
Description: This report presents a convenient method for calculating the pitching-moment characteristics of tapered wings with sweepback and twist. The method is based on the fact that the pitching-moment characteristics of a wing may be specified by giving the value of the pitching moment at zero lift and the location of the axis about which the axis is constant. Data for calculating these characteristics are presented by curves which apply to wings having a linear distribution of twist along the span and which cover a large range of aspect ratios. The curves are given for wings having straight taper and distorted elliptical plan forms. The characteristics of wings of other shapes may be determined by interpolation.
Contributing Partner: UNT Libraries Government Documents Department
Coal-Mine Accidents in the United States: 1931

Coal-Mine Accidents in the United States: 1931

Date: 1933
Creator: Adams, William W.; Geyer, L. E. & Chenoweth, L.
Description: Report compiled by the U.S. Bureau of Mines including statistics on fatal and non-fatal accidents in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
Contributing Partner: UNT Libraries Government Documents Department
Combustion in a high-speed compression-ignition engine

Combustion in a high-speed compression-ignition engine

Date: January 1, 1933
Creator: Rothrock, A M
Description: An investigation conducted to determine the factors which control the combustion in a high-speed compression-ignition engine is presented. Indicator cards were taken with the Farnboro indicator and analyzed according to the tangent method devised by Schweitzer. The analysis show that in a quiescent combustion chamber increasing the time lag of auto-ignition increases the maximum rate of combustion. Increasing the maximum rate of combustion increases the tendency for detonation to occur. The results show that by increasing the air temperature during injection the start of combustion can be forced to take place during injection and so prevent detonation from occurring. It is shown that the rate of fuel injection does not in itself control the rate of combustion.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of three methods for calculating the compressive strength of flat and slightly curved sheet and stiffener combinations

Comparison of three methods for calculating the compressive strength of flat and slightly curved sheet and stiffener combinations

Date: March 1, 1933
Creator: Lundquist, Eugene E
Description: This report gives a comparison of the accuracy of the three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressed-skin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffener and an effective width as a column gave the best agreement with the results of the tests. An investigation of the effect of small curvature resulted in the conclusion that the compressive strength of the curved panels is, for all practical purposes, equal to the strength of flat panels except for thick sheet where non-uniform curvature throughout the length may cause the strength of the curved panel to be 10 to 15 percent less than that of a corresponding flat panel.
Contributing Partner: UNT Libraries Government Documents Department
The Comper "Mouse" commercial airplane (British) : a three-seat cabin low-wing monoplane

The Comper "Mouse" commercial airplane (British) : a three-seat cabin low-wing monoplane

Date: October 1, 1933
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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