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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Collection: National Advisory Committee for Aeronautics Collection
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
Bending Tests of Metal Monocoque Fuselage Construction

Bending Tests of Metal Monocoque Fuselage Construction

Date: November 1930
Creator: Mossman, Ralph W. & Robinson, Russell G.
Description: Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Contributing Partner: UNT Libraries Government Documents Department
The Mureaux 111 R.2 military airplane (French) : a long-distance all-metal observation monoplane

The Mureaux 111 R.2 military airplane (French) : a long-distance all-metal observation monoplane

Date: April 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Shackleton-Murray SM-1 light airplane  : a two-place high-wing monoplane

The Shackleton-Murray SM-1 light airplane : a two-place high-wing monoplane

Date: June 1, 1933
Creator: NACA
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An approximate spin design criterion for monoplanes

An approximate spin design criterion for monoplanes

Date: June 1, 1939
Creator: Donlan, Charles J & Seidman, Oscar
Description: A quantitative criterion of merit has been needed to assist airplane designers to incorporate satisfactory spinning characteristics into new designs. An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, has been formulated in a recent British report. In the present paper, the British results have been analyzed and applied to American designs. A simpler design criterion based solely on the type and the dimensions of the tail, has been developed: it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning.
Contributing Partner: UNT Libraries Government Documents Department
The variation in pressure in the cabin of an airplane in flight

The variation in pressure in the cabin of an airplane in flight

Date: March 1, 1931
Creator: Gough, Melvin N
Description: The pressure in the cabin of a Fairchild cabin monoplane wa surveyed in flight, and was found to decrease with increased air speed over the fuselage and to vary with the number and location of openings in the cabin. The maximum depression of 2.2 inches of water (equivalent pressure altitude at sea level of 152 feet) occurred at the high speed of the airplane in level flight with the cabin closed.
Contributing Partner: UNT Libraries Government Documents Department
The Unsteady Lift of a Finite Wing

The Unsteady Lift of a Finite Wing

Date: January 1, 1939
Creator: Jones, Robert T
Description: Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less. The calculations indicate that the distribution of lift near the start is similar to the final distribution. Both the indicia and the oscillating lift functions are given. Approximate operational equivalents of the functions have been devised to facilitate the calculation of lift under various conditions of motion.
Contributing Partner: UNT Libraries Government Documents Department
The effect of cowling on cylinder temperatures and performance of a Wright J-5 engine

The effect of cowling on cylinder temperatures and performance of a Wright J-5 engine

Date: January 1, 1930
Creator: Schey, Oscar W & Biermann, Arnold E
Description: This report presents the results of tests conducted to determine the effect of different amounts and kinds of cowling on the performance and cylinder temperatures of a standard Wright J-5 engine. These tests were conducted in conjunction with drag and propeller tests in which the same cowlings were used. Four different cowlings were investigated varying from the one extreme of no cowling on the engine to the other extreme of the engine completely cowled and the cooling air flowing inside the cowling through an opening in the nose and out through an annular opening at the rear of the engine. Each cowling was tested at air speeds of approximately 60, 80, and 100 miles per hour.
Contributing Partner: UNT Libraries Government Documents Department
Further measurements of normal accelerations on racing airplanes

Further measurements of normal accelerations on racing airplanes

Date: February 1, 1936
Creator: KIRSCHBAUM H W & Scudder, N F
Description: The work of collecting acceleration data for racing airplanes during races, started in January 1934, has been continued by obtaining similar data in the airplanes winning first and second places in the 1935 Thompson Trophy Race. Records were taken in the Howard Racer "Mr. Mulligan" and in the Wittman D-12 Racer. The maximum positive accelerations were generally smaller than those recorded in other airplanes during earlier races; the maximum in the Howard Racer was 2.8 g, and one value of 4.25 g was obtained in the Wittman Racer. Minimum values were as low as -0.55 g in the Howard Racer and 0.3 g in the Wittman Racer.
Contributing Partner: UNT Libraries Government Documents Department
Nieuport-Delage 590 Military airplane (French) : a two-place high-wing cantilever monoplane

Nieuport-Delage 590 Military airplane (French) : a two-place high-wing cantilever monoplane

Date: November 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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