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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1933
 Collection: National Advisory Committee for Aeronautics Collection
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: January 1, 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 1, 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 1, 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 1, 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
Aerodynamic forces and moments of a seaplane on the water

Aerodynamic forces and moments of a seaplane on the water

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