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Additional design charts relating to the stalling of tapered wings

Description: From Introduction: "The present report, therefore, may be considered a supplement to reference 1. The combined scope of the stall charts of reference 1, designated A, and of the present work, designated B, is summarized in the following table: For the wing with root thickness ratio to 18 was also investigated.
Date: January 1943
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department
open access

Altitude Rating of Electrical Apparatus

Description: "This paper studies the effect of altitude on the ratings of rotating electric machines and after determining the fundamental principles involved, discusses these in relation to the application of such machines in modern aircraft" (p. 1).
Date: January 1943
Creator: Lebenbaum, Paul, Jr.
Partner: UNT Libraries Government Documents Department
open access

The Analysis of Strains Indicated by Multiple-Strand Resistance-Type Wire Strain Gages Used as Rosettes

Description: "Methods are given for making the necessary corrections to the strains indicated by multiple-strand resistance-type wire strain gages used singly or as rosettes to measure strains at an angle to the principal strain. The results of tests to determine the validity of the methods of correction are reported" (p. 1).
Date: January 1943
Creator: Dow, Norris F.
Partner: UNT Libraries Government Documents Department
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Chain Reaction of Pure Fissionable Materials in Solution

Description: The critical mass of 94-239 and the corresponding critical dimensions of homogeneous mixtures of 94-239 with various moderating media been calculated as a function of the concentration of 94. A simple transformation makes the figures applicated to92-235. the results are in essential agreement with the preliminary estimated made independently by Oppenheimer and Serber. The problem of the stability of a chain reaction in solution and questions of protection are discussed.
Date: January 1, 1943
Creator: Christy, Robert F., 1916-2012 & Wheeler, John Archibald, 1911-2008
Partner: UNT Libraries Government Documents Department
open access

Comparison of various methods for computing drag from wake surveys

Description: "The various equations for computing profile drag by the momentum method are examined, and the errors arising from complete or partial neglect of compressibility effects in the Jones equation and the Bicknell equation are evaluated. The integrating method of Silverstein and Katzoff is shown to be accurate over a wide range of Mach number and wake shapes" (p. 1).
Date: January 1943
Creator: Davis, Wallace F.
Partner: UNT Libraries Government Documents Department
open access

Derivation of charts for determining the horizontal tail load variation with any elevator motion

Description: Report presenting equations relating the wing and tail loads are derived for a unit elevator displacement. The equations are converted into a nondimensoinal form and charts are given that can be used to predict wing- and tail-load-increment variation for any type of elevator motion and for degrees of airplane stability.
Date: January 1943
Creator: Pearson, Henry A.
Partner: UNT Libraries Government Documents Department
open access

Drag Measurements of a Protruding.50-Caliber Machine Gun with Barrel Jacket Removed

Description: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effect… more
Date: January 1943
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Amphibious Floats on the Power-Off Stability and Control Characteristics of a Twin-Engine Cargo Airplane

Description: Report presenting power-off wind tunnel tests of a scale model of a twin-engine cargo airplane equipped with amphibious floats. Longitudinal and lateral stability and control characteristics were investigated for three flap positions.
Date: January 18, 1943
Creator: Belsley, Steven E. & Jackson, Roy P.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

Description: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It is shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients.
Date: January 1943
Creator: Allen, H. Julian & Nitzberg, Gerald E.
Partner: UNT Libraries Government Documents Department
open access

Effect of Fillers and of Mixing Procedure on the Strength of Plastic Materials

Description: Note presenting a study to prepare a series of molding powders with the use of a given plastic and given fillers in varying proportions and to determine the effect of the differences in composition of the molding powders on certain physical properties of standard test pieces molded from them.
Date: January 1943
Creator: Kynoch, William & Patronsky, L. A.
Partner: UNT Libraries Government Documents Department
open access

Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet

Description: "In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing th… more
Date: January 1943
Creator: Rafel, Norman
Partner: UNT Libraries Government Documents Department
open access

The Effect on Stability and Control of a Pusher Propeller Behind Conventional Tail Surfaces as Determined by Tests of a Powered Model in the Free-Flight Tunnel

Description: Report presenting an investigation of the effects on stability and control of a pusher propeller behind conventional horizontal and vertical tail surfaces in the free-flight tunnel by tests of a scale model of a submerged-engine pusher airplane. The investigation consisted of flight and balance tests at windmilling and high-power conditions with a partial-span Zap extensible flap extended and retracted. Results regarding the longitudinal stability, longitudinal control, stalling characteristics… more
Date: January 1943
Creator: Campbell, John P. & Hollingworth, Thomas A.
Partner: UNT Libraries Government Documents Department
open access

An experimental survey of flow across banks of elliptical and pointed tubes

Description: Report presenting an experimental survey of the details of the flow of fluids across banks of streamline tubes as a continuation of previous work. Information that clarifies the picture of flow has been obtained by surveys of total, dynamic, and static pressure, and hot-wire cooling surveys of the unheated tubes.
Date: January 1943
Creator: Joyner, Upshur T. & Palmer, Carl B.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of NACA D(Sub S) Cowlings on the XP-42 Airplane 1: High-Inlet-Velocity Cowling with Propeller Cuffs Tested in High-Speed Level Flight

Description: Report presenting results from a series of flight tests of the maximum speed and cooling characteristics in full-throttle level flight of the XP-42 airplane equipped with a short-nose high-inlet velocity cowling. The results of the tests indicated a maximum speed of 336 miles per hour at 960 horsepower at 25,000 feet. Results regarding maximum speed and pressure and temperatures are provided.
Date: January 1943
Creator: Bailey, F. J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 2: low-inlet-velocity cowling with axial-flow fan and propeller cuffs

Description: Report presenting results from a series of flight tests of the performance and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a short-nose low-inlet-velocity cowling and an axial-flow fan mounted on the spinner. Results regarding maximum speed and pressures and temperatures are provided.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 3: low-inlet-velocity cowling without fan or propeller cuffs, with axial-flow fan alone, and with two different sets of propeller cuffs

Description: Report presenting the results of flight measurements of performance and cooling characteristics of the XP-42 airplane equipped with a short-nose low-inlet-velocity cowling. Testing included measurements in level flight and climb of the effects of a spinner-mounted axial-flow fan without propeller cuffs, no fan or cuffs, and two different sets of propeller cuffs.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 4: high-inlet-velocity cowling tested in climb with and without propeller cuffs and in high-speed level flight without propeller cuffs

Description: Report presenting flight measurements of the performance and cooling characteristics of a short-nose high-inlet-velocity cowling on the XP-42 for conditions of climb with and without propeller cuffs and for high speed without cuffs. The speed of the airplane was approximately 1 mile per hour greater without propeller cuffs than the previously measured value with cuffs. Results regarding maximum speed, pressures and temperatures, and ground cooling are provided.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Effects of a Wing Leading-Edge Slot and Other Modifications on the Stability, Maximum Lift, and High Speed of an Observation Airplane

Description: Report presenting stability, maximum lift, and high-speed tests of an observation airplane fitted with Maxwell leading-edge slots. The static and dynamic longitudinal and lateral stability was generally satisfactory and not affected much by the slots.
Date: January 19, 1943
Creator: Turner, William N. & Adams, Betty
Partner: UNT Libraries Government Documents Department
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Full-Scale Tunnel Tests of a Flying Model of the Curtiss XP-55 Airplane

Description: Report presenting testing in the full-scale tunnel to provide data for estimating the longitudinal stability and control characteristics of the Curtis XP-55 airplane. Testing included lift, drag, pitching-moment, hinge-moment, and elevator pressure measurements for various combinations of angle of attack, elevator deflection, and elevator tab settings. The results of the force tests and some correlation of the results of the force tests and the pressure measurements are presented in the report.
Date: January 1943
Creator: Biebel, William J.
Partner: UNT Libraries Government Documents Department
open access

General free to trim tests in NACA tank no.2 of three 1/8-full-size models of flying-boat hulls at low speeds-NACA models 116E-3K, 120R, and 143

Description: Report presenting tests of representative models of flying boat hulls to determine the resistance at low speeds. Results regarding the effect of load coefficients, resistance coefficients, and towing and drifting calculations are provided.
Date: January 1943
Creator: Carter, Arthur W.
Partner: UNT Libraries Government Documents Department
open access

Generalized selection charts for bombers powered by two, four, and six 3000-horsepower engines 1: capacity and economy

Description: Supplement using data from a previous report to show the cargo that can be carried at various ranges, pounds of cargo that can be carried per pound of fuel, and other graphs to simplify the problem of determining which cargo can be carried at any range. The assumptions, parameters, and equations from the original report are carried over in the supplement.
Date: January 1943
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic-stability tests of a model of a flying boat and of a planing surface having a small downward projection (hook) on the planing bottom near the step

Description: Report presenting stability testing of two dynamic models in tank no. 1 in order to investigate the effects of adding a small projection, or hook, on the planing bottom of the forebody near the step of a seaplane. Tests with two different projections had a rather large effect on all of the trim limits and the landing stability.
Date: January 1943
Creator: Benson, James M.
Partner: UNT Libraries Government Documents Department
open access

Icing Tests of Aircraft-Engine Induction Systems

Description: Report presenting a program of icing tests conducted on an aircraft-engine induction system consisting of a Wright R-1820, G-200 blower section, Holley 1375-F carburetor and adapter, and specially built air scoop. The primary purpose of the investigation was to determine the effect of a number of possible factors on icing of engine-induction systems, including carburetor-air temperature, air-moisture content, water-droplet size, throttle opening, mixture ratio, rate of air flow, altitude, and o… more
Date: January 1943
Creator: Kimball, Leo B.
Partner: UNT Libraries Government Documents Department
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