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The Forces and Moments on Airplane Engine Mounts

Description: "A resume of the equations and formulas for the forces and moments on an aircraft-engine mount is presented. In addition, available experimental data have been included to permit the computation of these forces and moments. A sample calculation is made and compared with present design conditions for engine mounts" (p. 1).
Date: December 1936
Creator: Donely, Philip
Partner: UNT Libraries Government Documents Department
open access

Calculated Effect of Various Types of Flap on Take-Off Over Obstacles

Description: "In order to determine whether or not flaps could be expected to have any beneficial effect on take-off performance, the distances required to take off and climb to an altitude of 50 feet were calculated for hypothetical airplanes, corresponding to relatively high-speed types and equipped with several types of flap. The types considered are the Fowler wing, the Hall wing, the split flap, the balanced split flap, the plain flap, and the external-airfoil flap. The results indicate that substantia… more
Date: May 1936
Creator: Wetmore, J. W.
Partner: UNT Libraries Government Documents Department
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Boosted Performance of a Compression-Ignition Engine With a Displaced Piston

Description: From Summary: "Performance tests were made using a rectangular displacer arranged so that the combustion air was forced through equal passages at either end of the displacer into the vertical-disk combustion chamber of a single-cylinder, four-stroke-cycle compression-ignition test engine. After making tests to determine optimum displacer height, shape, and fuel-spray arrangement, engine-performance tests were made at 1,500 and 2,000 r.p.m. for a range of boost pressures from 0 to 20 inches of m… more
Date: May 1936
Creator: Moore, Charles S. & Foster, Hampton H.
Partner: UNT Libraries Government Documents Department
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Effect of changes in tail arrangement upon the spinning of a low-wing monoplane model

Description: "A series of tests was made in the N.A.C.A. free spinning tunnel to find the effect upon spinning characteristics of systematic changes in tail arrangement. The tests were made with a 1/16-scale made of a low-wing monoplane of modern design. The changes consisted of: (1) variation of the fuselage length; (2) variation of the fore-and-aft location of the vertical surfaces; and (3) variation of the vertical location of the horizontal surfaces. The spinning characteristics of the model, including … more
Date: June 1936
Creator: Zimmerman, C. H.
Partner: UNT Libraries Government Documents Department
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A method of estimating the aerodynamic effects of ordinary and split flaps of airfoils similar to the Clark Y

Description: An empirical method is given for estimating the aerodynamic effect of ordinary and split flaps on airfoils similar to the Clark Y. The method is based on a series of charts that have been derived from an analysis of existing wind-tunnel data. Factors are included by which such variables as flap location, flap span, wing aspect ratio, and wing taper may be taken into account. A series of comparisons indicate that the method would be suitable for use in making preliminary performance calculations… more
Date: June 1936
Creator: Pearson, H. A.
Partner: UNT Libraries Government Documents Department
open access

Performance of Air-Cooled Engine Cylinders Using Blower Cooling

Description: "An investigation was made to obtain information on the minimum quantity of air and power required to cool conventional air cooled cylinders at various operating conditions when using a blower. The results of these tests show that the minimum power required for satisfactory cooling with an overall blower efficiency of 100 percent varied from 2 to 6 percent of the engine power depending on the operating conditions. The shape of the jacket had a large effect on the cylinder temperatures. Increasi… more
Date: July 1936
Creator: Schey, Oscar W. & Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department
open access

Carbon-monoxide indicators for aircraft

Description: Several improvements that have been made on commercially available carbon-monoxide indicators to make them more suitable for aircraft use are described. These improvements include an automatic flow regulator, which permits the use of a simplified instrument on aircraft where a source of suction is available, and a more reliable alarm attachment. A field method for testing instruments on standard samples of carbon monoxide is described. Performance data and instructions in operation and maintena… more
Date: July 1936
Creator: Womack, S. H. J. & Peterson, J. B.
Partner: UNT Libraries Government Documents Department
open access

Combustion-engine temperatures by the sodium line-reversal method

Description: The sodium line-reversal method has been used in some preliminary measurements of flame temperature. Improvements in the method involving a photographic recorder and a means of correcting for the dirtiness of the windows are described. The temperatures so obtained are compared with those calculated from pressure diagrams.
Date: March 1936
Creator: Brevoort, Maurice J.
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Corrosion-Resistant Steel (18 Percent Chromium - 8 Percent Nickel) and Aluminum Alloy (24st)

Description: "In the selection of materials for aircraft application, it is not enough to make the selection on a strength-weight basis alone. A strength-weight comparison is significant but other factors must be considered, for while a material with a high ratio of strength to weight may be perfectly satisfactory for one use, it may be totally unfitted for another. It is essential, among other things, that the probable nature, magnitude, and direction of the principal stresses be given special consideratio… more
Date: March 1936
Creator: Sullivan, J. E.
Partner: UNT Libraries Government Documents Department
open access

Full-scale wind-tunnel to determine a satisfactory location for a service Pitot-static tube on a low-wing monoplane

Description: Surveys of the air flow over the upper surface of four different airfoils were made in the full-scale wind tunnel to determine a satisfactory location for a fixed Pitot-static tube on a low-wing monoplane. The selection was based on small interference errors, less than 5 percent, and on a consideration of structural and ground handling problems. The most satisfactory location on the airfoils without flaps that were investigated was 10 percent of the chord aft and 25 percent of the chord above t… more
Date: March 1936
Creator: Parsons, John F.
Partner: UNT Libraries Government Documents Department
open access

Remarks on the Elastic Axis of Shell Wings

Description: The definitions of flexural center, torsional center, elastic center, and elastic axis are discussed. The calculation of elastic centers is dealt with in principle and a suggestion is made for the design of shear webs.
Date: April 1936
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department
open access

Tank tests of models of floats for single-float seaplanes - First series

Description: "Large models of the Mark V and Mark VI floats used for single float seaplanes (National Advisory Committee for Aeronautics (NACA) models 41-A and 41-B, respectively) were tested in the NACA tank to provide general test data for typical single floats and a basis for possible improvements of their form. The resistance of model 41-B was greater than that of model 41-A, either when free to trim or at the best trim angle for each. The resistance of model 35-B (a pointed step hull tested free to tri… more
Date: April 1936
Creator: Parkinson, J. B.
Partner: UNT Libraries Government Documents Department
open access

Procedure for determining speed and climbing performance of airships

Description: From Summary: "The procedure for obtaining air-speed and rate-of-climb measurements in performance tests of airships is described. Two methods of obtaining speed measurements, one by means of instruments in the airship and the other by flight over a measured ground course, are explained. Instruments, their calibrations, necessary correction factors, observations, and calculations are detailed for each method, and also for the rate-of-climb tests. A method of correction for the effect on density… more
Date: April 1936
Creator: Thompson, F. L.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of Wing Flaps Suitable for Direct Control of Glide-Path Angle

Description: "Preliminary tests have been made for the purpose of obtaining a flap arrangement suitable for direct and immediate control of the steepness of the glide path of an airplane, a use for which present flaps are not satisfactory. An attempt has been made to develop a flap giving a reasonably high maximum lift coefficient with relatively low deflection and maintaining this value of the maximum lift coefficient with a large increase of deflection, the increase in deflection being accompanied by a la… more
Date: January 1936
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department
open access

Analysis and Model Tests of Autogiro Jump Take-Off

Description: From Introduction: "The possibilities of the jump take-off have been established by some full-scale experiments. It is the purpose of this paper to study the factors that govern the jump take-off in its simplest form and to present the results of model tests in which the effect of differences in the rotor parameters was determined."
Date: October 1936
Creator: Wheatley, John B. & Bioletti, Carlton
Partner: UNT Libraries Government Documents Department
open access

Notes on the technique of landing airplanes equipped with wing flaps

Description: "The proper landing of airplanes equipped with flaps, although probably no more difficult than landing without them, requires a different technique. The effects of flaps on the aerodynamics characteristics of a wing are given and, with the aid of figures and diagrams, a detailed comparison of the glide and landing of an airplane with and without flaps is made. The dangers attending improper execution and the importance of such factors as air speed fuselage attitude, glide-path angle, and contro… more
Date: January 1936
Creator: Gough, Melvin N.
Partner: UNT Libraries Government Documents Department
open access

Mixture Distribution in a Single-Row Radial Engine

Description: "The distribution of the fuel among the various cylinders of a Pratt and Whitney 1340 S1H1-G engine was determined by chemically analyzing samples of exhaust gas from each cylinder. The engine was operated in the 20-foot wind tunnel at different power outputs, specific fuel consumptions, and engine speeds. The results showed that the variation in the quality of the mixture among the different cylinders was approximately 4 percent and was independent of power output, specific fuel consumption, a… more
Date: October 1936
Creator: Gerrish, Harold C. & Voss, Fred
Partner: UNT Libraries Government Documents Department
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Circular Motion of Bodies of Revolution

Description: The circular motion for airship-like bodies has thus far been calculated only for a prolate ellipsoid of revolution (reference 1, p.133 and reference 2). In this paper, however, the circular motion of elongated bodies of revolution more nearly resembling airships will be investigated. The results will give the effect of rotation on the pressure distribution and thus yield some information as to the stresses set up in an airship in circular flight.
Date: February 1936
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department
open access

A general tank test of a model of the hull of the British Singapore IIC flying boat

Description: A general test was made in the N.A.C.A. tank of a 1/12-size model of the hull of the British Singapore IIC flying boat loaned by the Director of Research, British Air Ministry. The results are given in charts and are compared with the results of tests of a model of an American flying-boat hull, the Sikorsky S-40. The Singapore hull has a greater hump resistance but a much lower high-speed resistance than the S-40.
Date: September 1936
Creator: Dawson, John R. & Truscott, Starr
Partner: UNT Libraries Government Documents Department
open access

Limitations of the Pilot in Applying Forces to Airplane Controls

Description: Measurements were made to determine the relative maximum forces a pilot can exert on the controls of an airplane with the view of obtaining systematic data upon which to base the location of controls within the cockpit and the design of the control surfaces. A cockpit model of generous proportions, capable of being rotated to any attitude, was built with the location of the control stick and rudder pedals adjustable over a wide range of positions with respect to the seat. Besides measurements o… more
Date: January 1936
Creator: Gough, M. N. & Beard, A. P.
Partner: UNT Libraries Government Documents Department
open access

A study of autogiro rotor-blade oscillations in the plane of the rotor disk

Description: An analysis of the factors governing the oscillation of an autogiro rotor blade in the plane of the rotor disk showed that the contribution of the air forces to the resultant motion was small and that the oscillation is essentially a direct effect of the rotor-blade flapping motion. A comparison of calculated oscillations with those measured in flight on three different rotors disclosed that the calculations gave satisfactory agreement with experiment. The calculated air forces on the rotor bla… more
Date: September 1936
Creator: Wheatley, John B.
Partner: UNT Libraries Government Documents Department
open access

Tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise - NACA model 35 series

Description: From Summary: "The results of tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise are given in charts and are compared with results from tests of more conventional hulls. Increasing the angle of dead rise from 15 to 25 degrees: had little effect on the hump resistance; increased the resistance throughout the planning range; increased the best trim angle; reduced the maximum positive trimming moment required to obtain best trim angle; and h… more
Date: January 1936
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department
open access

Tank tests of models of flying boat hulls having longitudinal steps

Description: Four models with longitudinal steps on the forebody were developed by modification of a model of a conventional hull and were tested in the National Advisory Committee for Aeronautics (NACA) tank. Models with longitudinal steps were found to have smaller resistance at high speed and greater resistance at low speed than the parent model that had the same afterbody but a conventional V-section forebody. The models with a single longitudinal step had better performance at hump speed and as low hig… more
Date: July 1936
Creator: Allison, John M. & Ward, Kenneth E.
Partner: UNT Libraries Government Documents Department
open access

Estimation of moments of inertia of airplanes from design data

Description: "A method of determining the moments of inertia of an airplane from design data pertaining to the weights and locations of the component parts is described. The computations required to ascertain the center-of-gravity position are incorporated with the calculations of moments of inertia. A complete set of data and calculations for a modern airplane is given to illustrate the procedure. From a comparison between calculated values and measured values it is believed that the moments of inertia can… more
Date: July 1936
Creator: Kirschbaum, H. W.
Partner: UNT Libraries Government Documents Department
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