National Advisory Committee for Aeronautics (NACA) - 95 Matching Results

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The aerodynamic safety of airplanes

Description: This report presents several hypotheses regarding airplane safety, mainly concerning the nondimensional coefficient of air, speed, acceleration, and wing area on aerodynamic considerations of safety.
Date: September 1932
Creator: Kahn, Louis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An airfoil spanning an open jet

Description: From Summary: "The first part of the report treats of the theory involved. The second part describes the experiments performed for the purpose of proving the theory."
Date: September 1933
Creator: Stüper, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airplane Stability in Taxying

Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
Date: September 1932
Creator: Anderlik, E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Airspeed "Oxford" Training Airplane (British): A Two-Engine Cantilever Monoplane

Description: Circular describing the Airspeed A.S. 10 "Oxford", which is a twin-engine trainer with a variety of equipment, including propellers, landing gear, and other components.Details of the wings, fuselage, the inside, characteristics, performance, drawings, and photographs are provided.
Date: September 1937
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Alterations and Tests of The "Farnboro" Engine Indicator

Description: "The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of p… more
Date: September 1930
Creator: Collins, John H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Avro C.30 Direct-Control Autogiro (British)

Description: Circular describing the Avro C.30 direct-control autogiro. Details of the construction, fuselage, engine mounting, tail, cockpits, rotor system, characteristics, performance, drawings, and photographs are provided.
Date: September 1934
Creator: Colson, C. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Breguet 270 General-Purpose Military Airplane (French): A Two-Seat All-Steel Sesquiplane

Description: Circular presenting a description of the Breguet 270 general-purpose military airplane, which is a two-set, all-steel sesquiplane. Details regarding the basic principles of design, construction, components, flying qualities, drawings, and photographs are provided.
Date: September 1930
Creator: De Marolles, R. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Breguet Military Airplane, Type 33: A Two-Place Long-Distance Sesquiplane for Observation and Bombing

Description: Circular presenting a description of the Breguet military airplane, Type 33, which is a two-place long-distance sesquiplane made for observation and bombing. Details of the components, bomb dropping, flying qualities, design, flying qualities and performances, drawings, and photographs are provided.
Date: September 1931
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for Calculating the Performance of Airplanes Having Constant-Speed Propellers

Description: "Charts are presented for determining the performance of airplanes having variable-pitch propellers, the pitch of which is assumed to be adjusted to maintain constant speed for all rates of flight. The charts are based on the general performance equations developed by Oswald in reference 1, and are used in a similar manner. Examples applying the charts to airplanes having both supercharged and unsupercharged engines are included" (p. 1).
Date: September 1936
Creator: White, Roland J. & Martin, Victor J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Coefficients of discharge of fuel-injection nozzles for compression-ignition engines

Description: "This report presents the results of an investigation to determine the coefficients of discharge of nozzles with small, round orifices of the size used with high-speed compression-ignition engines. The injection pressures and chamber back pressures employed were comparable to those existing in compression-ignition engines during injection. The construction of the nozzles was varied to determine the effect of the nozzle design on the coefficient. Tests were also made with nozzles assembled in an… more
Date: September 11, 1930
Creator: Gelalles, A. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Column Strength of Tubes Elastically Restrained Against Rotation at the Ends

Description: Report presents the results of a study made of the effects of known end restraint on commercially available round and streamline tubing of chromium-molybdenum steel, duralumin, stainless steel, and heat-treated chromium-molybdenum steel; and a more accurate method than any previously available, but still a practical method, was developed for designing compression members in riveted or welded structures, particularly aircraft. Two hundred specimens were tested as short, medium-length, and long c… more
Date: September 9, 1937
Creator: Osgood, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Column Strength of Two Extruded Aluminum-Alloy H-Sections

Description: "Extruded aluminum-alloy members of various cross sections are used in aircraft as compression members either singly or as stiffeners for aluminum-alloy sheet. In order to design such members, it is necessary to know their column strength or, in the case of stiffeners, the value of the double modulus, which is best obtained for practical purposes from column tests. Column tests made on two extruded h-sections are described, and column formulas and formulas for the ratio of the double modulus to… more
Date: September 30, 1938
Creator: Osgood, William R. & Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combined Beam-Column Stresses of Aluminum-Alloy Channel Sections

Description: The results of a research program to obtain design data on the strength of open-channel aluminum-alloy sections subjected to combined column and beam action. The results of the tests of about 70 specimens were graphed for stresses due to axial load and stresses due to bending loading as functions of length to radius of gyration of the specimens. From these graphs a design chart was derived that is suitable for ready use.
Date: September 1939
Creator: Gottlieb, R.; Thompson, T. M. & Witt, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A complete tank test of a model of a flying-boat Hull - N.A.C.A. model no.11-A

Description: Model No. 11-A was designed as an improvement over N.A.C.A. Model No. 11, a complete test of which is described in N.A.C.A. Technical Note No. 464. In contrast with the longitudinal upward curvature in the planing bottom forward of the main step on Model 11-A was made as flat as practicable. Otherwise, the two models have very nearly the same form. The results of towing tests made on Model 11-A in the N.A.C.A. tank over a wide range of speed, load on the water, and trim angle are presented, bot… more
Date: September 1933
Creator: Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Complete Tank Test of a Model of Flying-Boat Hull - N.A.C.A. Model 16

Description: "A model of a 2-step flying-boat hull, of the type generally used in England, was tested according to the complete method described in the N.A.C.A. Technical Note No. 464. The lines of this model were taken from offsets given by Mr. William Munro in Flight, May 29, 1931. The data cover the range of loads, speeds, and trim angles that may be of use in applying the hull form to the design of any seaplane. The results are reduced to nondimensional form to aid application to design problems and fac… more
Date: September 1933
Creator: Shoemaker, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Complete tank tests of two flying-boat hulls with pointed steps - N.A.C.A. Models 22-A and 35

Description: "This note presents the results of complete tank test of N.A.C.A. Models 22-A and 35, two flying-boat hulls of the deep pointed-step type with low dead rise. Model 22-A is a form derived by modification of Model 22, the test results of which are given in N.A.C.A. Technical Note No. 488. Model 35 is a form of the same type but has a higher length-beam ratio than either Model 22 or 22-A. Take-off examples are worked out using data from these tests and a previous test of a conventional model appli… more
Date: September 1934
Creator: Shoemaker, James M. & Bell, Joe W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Contribution to the Mutual Interference of Wing and Propeller

Description: "The change of induced wing drag due to the field of flow of the propeller was analyzed quantitatively. The field of flow of the propeller is represented by a uniform distribution of sinks over the propeller disk area, whose strength is determined by the increase in speed in the slipstream. The superposition of this sink flow on the basic flow reproduces the actual field of flow outside of the slipstream with close approximation" (p. 1).
Date: September 1934
Creator: Wieselsberger, C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Controls at Low Hinge Moments

Description: A very stable airplane remains very maneuverable when the hinge moments of the controls remain inferior to those obtained with the conventional forms and when the wing lift at high angles has been improved. From this point of view, elevators balanced by recoil of the hinge, and slotted wings present some interesting features. The results of testing with several different types of wings and tail surfaces are provided.
Date: September 1932
Creator: Pris, M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Dangerous Sideslip of a Stalled Airplane and Its Prevention

Description: This investigation covers only that phase of airplane accidents which are the result of sideslip. We examine the circumstances under which this occurs, study the behavior of present-day airplane types (monoplane, conventional and staggered biplane) therein and endeavor to find a solution whereby this danger may be avoided.
Date: September 1931
Creator: Fuchs, Richard & Schmidt, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A deflection formula for single-span beams of constant section subjected to combined axial and transverse loads

Description: In this paper there is presented a deflection formula for single-span beams of constant section subjected to combined axial and transverse loads of the types commonly encountered in airplane design. The form of the equation is obtainable by dimensional analysis. Tables and curves of the non dimensional coefficients are appended to facilitate the use of the formula. The equation is applied to the determination of the spring constant of a beam. Tables and curves are presented to show the variatio… more
Date: September 1935
Creator: Burke, Walter F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Details of the Construction and Production of Fuel Pumps and Fuel Nozzles for the Airplane Diesel Engine

Description: This report presents investigations into the design and construction of fuel pumps for diesel engines. The results of the pump tests on the engines showed that, with a good cut-off, accurate injection, assured by the proper adjustment of the pump elements, there is a decrease in the consumption of fuel and hence an increase in the rated power of the engine. Some of the aspects investigated include: cam profile, coefficient of discharge, and characteristics of the injection system.
Date: September 1936
Creator: Lubenetsky, W. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of the Maximum Control Forces and Attainable Quickness in the Operation of Airplane Controls

Description: "This report is intended to furnish bases for load assumptions in the designing of airplane controls. The maximum control forces and quickness of operation are determined. The maximum forces for a strong pilot with normal arrangement of the controls is taken as 1.25 times the mean value obtained from tests with twelve persons. Tests with a number of persons were expected to show the maximum forces that a man of average strength can exert on the control stick in operating the elevator and ailero… more
Date: September 1930
Creator: Hertel, Heinrich
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The development, design and construction of gliders and sailplanes

Description: This report explains and details the history of glider design and construction through the impetus of the Rhon Sailplane contests. Some of the topics considered include: whether the longitudinal stability (dynamic and static) is sufficient in the tailless typo and a consideration that the structural weight of sweptback wings would be greater than that of a corresponding normal wing.
Date: September 1931
Creator: Lippisch, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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