National Advisory Committee for Aeronautics (NACA) - 39 Matching Results

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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Considerations of the Take-Off Problem

Description: Many technical papers on the various phases of airplane take-off have been published. Frequently, however, there appear new ideas which affect only particular scattered phases of the subject and which do not receive individual publication. It is the purpose of this paper to present several ideas of this nature which may be of considerable aid in calculating take-off performance and one idea which should correct what appears to be a popular misconception of the importance of static propeller thr… more
Date: February 1936
Creator: Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Further Measurements of Normal Accelerations on Racing Airplanes

Description: This report details the acceleration data collected from racing airplanes during actual races. The data was collected in order to make recommendations regarding the structural safety of racing airplanes and the methods of operating racing airplanes that reduces the probability of subjecting them to extreme air loads. The records do not lead to any conclusions regarding maximum air loads.
Date: February 1936
Creator: Kirschbaum, H. W. & Scudder, N. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Piloting technique for recovery from spins

Description: "Systematic flight investigation of the spinning characteristics of various airplanes over a period of several years have given the pilots engaged in the testing a varied and extensive experience. From this experience certain general rules of procedure have been formulated, particularly for the sequence of operation of the controls in recovery from spins, and are recommended to the attention of all pilots" (p. 1).
Date: February 1936
Creator: McAvoy, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Performance of a DePalma Roots-Type Supercharger

Description: "The results of tests made to determine the performance of a DePalma-Roots supercharger are presented. The performance of the DePalma supercharger with atmospheric pressure at the discharge was compared with that of a hypothetical NACA Roots-type supercharger of the same displacement. The tests were conducted at speeds from 1,000 to 6,000 r.p.m. and at pressure differences from 0 to 15 inches of mercury" (p. 1).
Date: March 1936
Creator: Schey, Oscar W. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Influence of Fuel-Oil Temperature on the Combustion in a Prechamber Compression-Ignition Engine

Description: Note presenting the influence of fuel-oil temperature on combustion as investigated by injecting the fuel into the prechamber of a single-cylinder, 4-stroke-cycle, water-cooled, compression-ignition engine operating at 1500 rpm and at a compression ratio of 13.5. The results showed that heating the fuel oil to 750 degrees Fahrenheit increased the injection period, changed the rate of injection, and eliminated the spray cone.
Date: April 1936
Creator: Gerrish, Harold C. & Ayer, Bruce E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Tests of a Model of the NC Flying-Boat Hull - N.A.C.A. Model 44

Description: "A 1/7.06 full-size model of the NC-type hull was tested in the N.A.C.A. tank by both the general method and the specific or free-to-trim method. The results of the tests are given in curves plotted as non dimensional coefficients and are compared with the test results of N.A.C.A. model 11-A. The NC model (N.A.C.A. model 44) shows higher resistance than model 11-A at hump speed but lower resistance at high speeds. Model 44 has a higher best trim angle at the jump and a lower maximum positive tr… more
Date: May 1936
Creator: Bell, Joe W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of N.A.C.A. airfoils in the variable-density wind tunnel. Series 230

Description: The results of tests of six airfoils having the N.A.C.A. 230 mean line and varying in thickness from 0.06c to 0.21c are presented. These results agree with previous findings in showing that aerodynamically the best section is one of moderate thickness. The data are of value mainly in connection with the design of tapered wings having sections based on the N.A.C.A. 230 mean line.
Date: May 1936
Creator: Jacobs, Eastman N. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Approximate Spin Design Criterion for Monoplanes

Description: "An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, was formulated. The British results were analyzed and applied to American designs. A simpler design criterion, based solely on the type and the dimensions of the tail, was 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" (p. 1).
Date: June 1936
Creator: Seidman, Oscar & Donlan, Charles J.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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