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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1925
 Collection: National Advisory Committee for Aeronautics Collection
The calculation of wing float displacement in single-float seaplanes

The calculation of wing float displacement in single-float seaplanes

Date: March 1, 1925
Creator: Warner, Edward P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The velocity distribution caused by an airplane at the points of a vertical plane containing the span

The velocity distribution caused by an airplane at the points of a vertical plane containing the span

Date: March 1, 1925
Creator: Munk, Max M
Description: A formula for the computation of the vertical velocity component on all sides of an airplane is deduced and discussed. The formation is of value for the interpretation of such free flight tests where two airplanes fly alongside each other to facilitate observation.
Contributing Partner: UNT Libraries Government Documents Department
Pressure distribution on the nose of an airship in circling flight

Pressure distribution on the nose of an airship in circling flight

Date: August 1, 1925
Creator: Fairbanks, Karl J
Description: In recent tests on the pressures occurring on the envelope and control surfaces of the naval airship C-7, it was noted that the pressures on the nose of the airship, while flying in level circling flight, were symmetrically distributed. Such a condition can only occur when the nose of the airship is pointed directly into the wind, and to accomplish this in circling flight, the axis of the airship must then be parallel to the direction of the motion of the nose. The question was raised as to whether the same conditions occur generally on all airships in circling flight. It appears that airships flying in a constant, level, circling flight path will generally head very closely into the wind, and any deviation will be so slight that the distribution of pressure over the nose will be but slightly, if at all, changed from a symmetrical distribution.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of fuselages and windshields

Wind tunnel tests of fuselages and windshields

Date: September 1, 1925
Creator: Warner, Edward P
Description: The tests described herein were made in 1918, in the old four-foot wind tunnel at the Massachusetts Institute of Technology and at the request of the Engineering Division of the U.S. Army Air Service. The results were given circulation only in official circles at that time. The interest of the work appears sufficient to justify its wider distribution even at this very late date.
Contributing Partner: UNT Libraries Government Documents Department
Propeller scale effect and body interference

Propeller scale effect and body interference

Date: September 1, 1925
Creator: Weick, Fred E
Description: This note shows that the main part of the discrepancy between full flight propeller performance and the performance of models in a wind tunnel is due to a scale effect, and that a minor part is caused by body interference. Analyses are made of propeller performances on several standard airplanes, and the actual brake horsepower compared with the power as calculated from model test data. The calculated power is based on that absorbed by a wind tunnel propeller model which is geometrically similar to the full scale propeller and is operating under the same ratio of V/nD.
Contributing Partner: UNT Libraries Government Documents Department
Note on the air forces on a wing caused by pitching.

Note on the air forces on a wing caused by pitching.

Date: March 1, 1925
Creator: Munk, Max M
Description: The following contains information on the air forces on a wing produced by it's pitching at a finite rate of angular velocity. The condition of smooth flow at the region of the trailing edge is maintained. The wing then experiences the same lift as if moving with the momentary velocity of the rear edge.
Contributing Partner: UNT Libraries Government Documents Department
The comparison of well-known and new wing sections tested in the variable density wind tunnel

The comparison of well-known and new wing sections tested in the variable density wind tunnel

Date: May 1, 1925
Creator: Higgins, George J
Description: Three groups of airfoils have been tested in the variable density wind tunnel. The first group contains three airfoils. The second group is a systematic series of twenty-seven airfoils. The third group consists of several frequently used wing sections.
Contributing Partner: UNT Libraries Government Documents Department
The estimation of airplane performance from wind tunnel tests on conventional airplane models

The estimation of airplane performance from wind tunnel tests on conventional airplane models

Date: May 1, 1925
Creator: Warner, Edward P
Description: Calculations of the magnitude of the correction factors and the range of their variations for wind tunnel models used in making aircraft performance predictions were made for 23 wind tunnel models. Calculated performances were compared with those actually determined for such airplanes as have been built and put through flight test. Except as otherwise noted, all the models have interplane struts and diagonal struts formed to streamwise shape. Wires were omitted in all cases. All the models were about 18 inches in span and were tested in a 4-foot wind tunnel. Results are given in tabular form.
Contributing Partner: UNT Libraries Government Documents Department
The drift of an aircraft guided towards it's destination by directional receiving of radio signals transmitted from the ground

The drift of an aircraft guided towards it's destination by directional receiving of radio signals transmitted from the ground

Date: June 1, 1925
Creator: unknown
Description: Following a curved path increases the distance to be flown, and a type of radio navigation that forces the adoption of such a path is therefore less efficient than one that marks out a definite straight line between the point of departure and the intended destination, and holds the airplane to that line. To determine the loss of efficiency resulting from curvature of the path, calculations were made for two particular cases by the method of step-by-step integration. The calculations were based on the assumption that the pilot makes straightforward use of his radio for navigation and makes no allowance for drift. Results are given in tabular form for two airplanes flying 200 miles at 100 mph, one with a cross wind of 50 mph wind across course, and the other with a 20 mph wind across course. It is shown that the following of the curved path increases the time of flight and the air distance flown by 17 percent and 2.5 percent in the two cases.
Contributing Partner: UNT Libraries Government Documents Department
Note on the Katzmayr effect on airfoil drag

Note on the Katzmayr effect on airfoil drag

Date: February 1, 1925
Creator: Ober, Shatswell
Description: The reduction of drag of an airfoil when the air stream is oscillating is called the Katzmayr effect. The purpose here is to offer a simple explanation of the cause of the Katzmayr effect.
Contributing Partner: UNT Libraries Government Documents Department
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