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 Collection: National Advisory Committee for Aeronautics Collection
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Three methods of calculating range and endurance of airplanes

Three methods of calculating range and endurance of airplanes

Date: January 1927
Creator: Diehl, Walter S.
Description: This report develops new equations which give the range and endurance of airplanes with an accuracy equal to that obtained from a step-by-step integration of the flight. A method of obtaining equally satisfactory results from Brequet's equations is also given in detail. A third method of calculating range and endurance, derived by the writer for use in routine estimating in the Bureau of Aeronautics, is also given in full. The reports contains tables and curves arranged for convenient use and illustrates the three methods by comparative estimates.
Contributing Partner: UNT Libraries Government Documents Department
A study of the effect of a diving start on airplane speed

A study of the effect of a diving start on airplane speed

Date: January 1926
Creator: Diehl, Walter S.
Description: Equations for instantaneous velocity and distance flown are derived for an airplane which crosses the starting line of a speed course at a speed higher than that which can normally be maintained in horizontal flight. A specific case is assumed and calculations made for five initial velocities. Curves of velocity, average velocity, and distance flown are plotted against time for each case and analyzed. It is shown that the increase in average velocity due to a diving start may be very large for short-speed courses.
Contributing Partner: UNT Libraries Government Documents Department
Collection of wind-tunnel data on commonly used wing sections

Collection of wind-tunnel data on commonly used wing sections

Date: January 1930
Creator: Louden, F. A.
Description: This report groups in a uniform manner the aerodynamic properties of commonly used wing sections as determined from tests in various wind tunnels. The data have been collected from reports of a number of laboratories. Where necessary, transformation has been made to the absolute system of coefficients and tunnel wall interference corrections have been applied. Tables and graphs present the data in the various forms useful to the engineer in the selection of a wing section.
Contributing Partner: UNT Libraries Government Documents Department
The torsional strength of wings

The torsional strength of wings

Date: January 1930
Creator: Burgess, C. P.
Description: This report describes a simple method for calculating the position of the elastic axis of a wing structure having any number of spars. It is shown that strong drag bracing near the top and bottom of a wing greatly increases the torsional strength. An analytical procedure for finding the contribution of the drag bracing to the torsional strength and stiffness is described, based upon the principle of least work, and involving only one unknown quantity. A coefficient for comparing the torsional rigidity of different wings is derived in this report.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of take-off run

The calculation of take-off run

Date: January 1934
Creator: Diehl, Walter S.
Description: A comparatively simple method of calculating length of take-off run is developed from the assumption of a linear variation in net accelerating force with air speed and it is shown that the error involved is negligible.
Contributing Partner: UNT Libraries Government Documents Department
Flight tests on U.S.S. Los Angeles. Part II : stress and strength determination

Flight tests on U.S.S. Los Angeles. Part II : stress and strength determination

Date: January 1930
Creator: Burgess, C. P.
Description: The tests described in this report furnished data on the actual aerodynamic forces, and the resulting stresses and bending moments in the hull of the U. S. S. "Los Angeles" during as severe still-air maneuvers as the airship would normally be subjected to, and in straight flight during as rough air as is likely to occur in service, short of squall or storm conditions. The maximum stresses were found to be within the limits provided for in accepted practice in airship design. Normal flight in rough air was shown to produce forces and stresses about twice as great as the most severe still-air maneuvers. No light was thrown upon the forces which might occur in extreme or exceptional conditions, such as the storm which destroyed the "Shenandoah". The transverse aerodynamic forces on the hull proper were found to be small and irregular. Owing to the necessity of conserving helium, it was impossible to fly the airship in a condition of large excess of buoyancy or weight in order to determine the air pressure distribution at a fixed angle of pitch. However, there is every reason to believe that in that condition the forces on the actual airship are as close ...
Contributing Partner: UNT Libraries Government Documents Department
Handley Page metal construction

Handley Page metal construction

Date: October 1, 1929
Creator: unknown
Description: In this report Handley Page construction techniques are shown such as: solid-drawn tubular duralumin spars are used in the stabilizer; plain channel sections are used extensively for minor components; and the manner of assembling them into a stabilizer compression strut is shown.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

Date: January 1, 1952
Creator: Macks, E Fred & Nemeth, Zolton N
Description: A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made by means of a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and the outer-race bearing operating temperatures are computed for the laboratory test rig and the turbojet engine. A method is given that enables the designer to predict the inner- and outer-race turbine roller-bearing temperatures from single curves, regardless of variations in speed, load, oil flow, oil inlet temperature, oil inlet viscosity, oil-jet diameter, or any combination of these parameters.
Contributing Partner: UNT Libraries Government Documents Department
Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil

Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil

Date: January 1, 1933
Creator: Clay, William C & Theodorsen, Theodore
Description: This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both in the laboratory and in flight show conclusively that it is necessary to heat only the front portion of the wing surface to effect complete prevention. Experiments in flight show that a vapor-heating system which extracts heat from the exhaust and distributes it to the wings is an entirely practical and efficient method for preventing ice formation.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigations concerning the limits of detonation in gaseous mixtures.  Part I

Experimental investigations concerning the limits of detonation in gaseous mixtures. Part I

Date: February 1, 1930
Creator: Wendlandt, Rudolf
Description: It is the purpose of this investigation to determine quantitatively the limits of detonation in gaseous mixtures for the conditions imposed and for a number of given gaseous explosive mixtures.
Contributing Partner: UNT Libraries Government Documents Department