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On the plane potential flow past a symmetrical lattice of arbitrary airfoils

Description: Report presenting a theoretical investigation of the two-dimensional, incompressible potential flow past a symmetrical lattice of airfoils of arbitrary shape. Expressions are given for evaluation of the velocity and pressure distribution at the airfoil boundary.
Date: January 1944
Creator: Garrick, I. E.
Partner: UNT Libraries Government Documents Department
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Compressible potential flow with circulation about a circular cylinder

Description: Report presenting the potential function for flow, with circulation, of a compressible fluid about a circular cylinder, which is obtained in series form including terms of the order of M(exp 4) where M is the Mach number of the free stream. The equations are used to obtain pressure coefficient as a function of Mach number at a point on the surface of the cylinder for different values of circulation.
Date: January 1944
Creator: Heaslet, Max A.
Partner: UNT Libraries Government Documents Department
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Tolerance concentration of radioactive gases in air

Description: The effects of ionizing radiation on the lung, specifically the bronchial tubes, were discussed relative to the incidence of lung cancer in radium miners. The energy transferred to the epithelium by inhaled radon was calculated, and the steps in the process leading to the initiation of cancer were described. (ACR)
Date: January 1, 1944
Creator: Failla, G.
Partner: UNT Libraries Government Documents Department
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Turbidity Flocculation in Columbia River Water

Description: This document contains data about the Columbia River water acquired January 9, 1944. The discussion includes: laboratory tests for turbidity and flocculation with aluminum.
Date: January 9, 1944
Creator: Frank, R. D. & Conley, W. R.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of hinge-moment characteristics of spring-tab ailerons

Description: Report presenting testing in the stability tunnel of two types of spring tab used as balances on a partial-span plain aileron. The tabs were connected to a spring located in the control system so that tab deflection was dependent on the control force.
Date: January 1944
Creator: Imlay, Frederick H. & Bird, J. D.
Partner: UNT Libraries Government Documents Department
open access

Collection of Balanced-Aileron Test Data

Description: "Test data of balanced ailerons have been collected from NACA and British sources. These data, which are presented in the form of charts, are grouped as A - ailerons with Frise balances, B - ailerons with blunt-nose balances, C - ailerons with internal balances, D - ailerons with contour modifications, and E - ailerons with tabs. Results of flight tests and of wind-tunnel tests in both two- and three-dimensional flow are presented but no correlation nor resume of the data has been included" (p.… more
Date: January 1944
Creator: Rogallo, F. M.
Partner: UNT Libraries Government Documents Department
open access

An investigation of aircraft heaters 15: the emissivity of several materials

Description: Report presenting a determination of the mean effective emissivity as a function of temperature for the surfaces of several metals and insulating materials. A description and discussion of the measuring technique is presented. The results are plotted on a variety of graphs.
Date: January 1944
Creator: Boelter, L. M. K.; Bromberg, R. & Gier, J. T.
Partner: UNT Libraries Government Documents Department
open access

A Theoretical Investigation of the Rolling Oscillations of an Airplane With Ailerons Free

Description: Report discusses an analysis of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. Information about the aerodynamic balance of the plane and oscillations that may be encountered are included. The effects of friction in the control system is also explored.
Date: January 1944
Creator: Cohen, Doris
Partner: UNT Libraries Government Documents Department
open access

On the flow of a compressible fluid by the hodograph method 1: unification and extension of present-day results

Description: From Summary: "Elementary basic solutions of the equations of motion of a compressible fluid in the hodograph variables are developed and used to provide a basis for comparison, in the form of velocity correction formulas, of corresponding compressible and incompressible flows. The known approximate results of Chaplygin, Von Karman and Tsien, Temple and Yarwood, and Prandtl and Glauert are unified by means of the analysis of the present paper. Two new types of approximations, obtained from the … more
Date: January 12, 1944
Creator: Garrick, I. E. & Kaplan, Carl
Partner: UNT Libraries Government Documents Department
open access

Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power

Description: Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that t… more
Date: January 1944
Creator: Rothrock, Addison M.
Partner: UNT Libraries Government Documents Department
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Effect of Inlet-Air Temperature and Cylinder Displacement on Charge Temperature of Internal Combustion Engines

Description: Report discussing the effect of inlet-air temperature and cylinder displacement on the charge temperature of an internal-combustion engine at the end of the induction stroke. The experiment to test various types of cylinders and their results on the air temperature and pressure is described.
Date: January 1944
Creator: Sanders, Newell D. & Bolz, Ray E.
Partner: UNT Libraries Government Documents Department
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Note on the Interpretation of Wake-Survey Data and Its Use in the Estimation of Induced Drag Due to Irregularities

Description: "An analysis of the irregular vertical displacement of the wake from the trailing edge of a tailless airplane is presented, which shows the existence of an effective aerodynamic wing twist that causes an induced drag coefficient of 0.0004. The analysis explains most of the discrepancy between the drag determined from the momentum surveys an the drag measured on the wind-tunnel balance" (p. 1).
Date: January 1944
Creator: Katzoff, S. & Finn, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the NACA 4-(3)(8)-045 Two-Blade Propellers at Forward Mach Numbers to 0.725 to Determine the Effects of Compressibility and Solidity on Performance

Description: From Summary: "As part of a general investigation of propellers at high forward speeds, tests of two 2-blade propellers having the NACA 4-(3)(8)-03 and NACA 4-(3)(8)-45 blade designs have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.725 to establish in detail the changes in propeller characteristics due to compressibility effects. These propellers differed primarily only in blade solidity,… more
Date: January 22, 1944
Creator: Stack, John; Draley, Eugene C.; Delano, James B. & Feldman, Lewis
Partner: UNT Libraries Government Documents Department
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Comparison of an approximate and an exact method of shear-lag analysis

Description: Report presenting comparisons between the approximate substitute single-stringer method of shear-lag analysis and the exact solutions, which indicate that for beams of practical proportions the approximate method yields a value for the maximum root stress that exceeds the value obtained by use of the exact solution by less than 10 percent.
Date: January 1944
Creator: Duberg, John E.
Partner: UNT Libraries Government Documents Department
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Shear-Lag Tests of Two Box Beams With Corrugated Covers Loaded to Failure

Description: "Strain measurements were made on the compression side of two box beams with corrugated aluminum-alloy covers loaded to failure. Angles formed from sheet were used for corner flanges in beam 1; whereas extruded angles were used in beam 2. Failure in each beam occurred in the corner angle at a stress that was above the compressive yield stress for the material" (p. 1).
Date: January 1944
Creator: Chiarito, Patrick T.
Partner: UNT Libraries Government Documents Department
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Determination of the Effect of Wing Flexibility on Lateral Maneuverability and a Comparison of Calculated Rolling Effectiveness With Flight Results

Description: Report presenting an analysis which shows that, when account is taken of sideslip and wing flexibility, the calculated rolling maneuverability of an airplane is in good agreement with the results obtained from flight tests. The method used avoids the complications of successive approximations but is nevertheless believed to be more nearly accurate than other methods based on semirigid-wing assumptions. The method is applied to a wing of tubular shell construction and the procedure is illustrate… more
Date: January 1944
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department
open access

High-Speed Aerodynamic Characteristics of a Four-Engine Transport Airplane as Determined From Tests of a 0.075-Scale Model

Description: Report presenting tests made in order to determine the differences in high-speed aerodynamic characteristics between models of a four-engine transport airplane and a similar bomber airplane. The main conclusion found is that the critical Mach number of the transport model is about 0.05 less than that of the bomber model.
Date: January 1944
Creator: Barnes, Robert H.
Partner: UNT Libraries Government Documents Department
open access

Tests of Thermal-Electric De-Icing Equipment for Propellers

Description: "Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius" (p.… more
Date: January 1944
Creator: Scherrer, Richard & Rodert, Lewis A.
Partner: UNT Libraries Government Documents Department
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A Method for Welding Sheet Aluminum to SAE 4140 Steel

Description: Report presenting an investigation of a large variety of different metals used as an intermediate metal between aluminum and steel for the purpose of securing a good bond both from the viewpoint of strength and thermal conductivity. The principal result was that it was found possible to secure a satisfactory bond between aluminum and steel by electroplating the steel with a layer of silver of proper thickness.
Date: January 1944
Creator: Hess, W. F. & Nippes, E. F., Jr.
Partner: UNT Libraries Government Documents Department
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Temperature Rise in a Heat Producing Cylinder Under a Coating Defect

Description: Abstract: "For defects between interior and coating, or between successive layers of coating, a simple, fairly accurate formula is established. The temperature rise at the edge of the defect is briefly discussed."
Date: January 25, 1944
Creator: Ginsburg, M.; Karush, W. & Young, G.
Partner: UNT Libraries Government Documents Department
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The Statistics of the Hypocritical Water Boiler

Description: From introductory paragraph: "In a slightly hypocritical water boiler the introduction of a single neutron may give rise to a fairly large burst of neutrons which dies out slowly. As was shown some time ago by Frankel and Nelson with the help of A. Horn the statistics of this multiplication process can be treated in a simple way for the hypothetical case that the number of neutrons produced per fission is two."
Date: January 8, 1944
Creator: Frankel, S. P.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of ailerons on a low-drag airfoil 1: The effect of aileron profile

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20-chord plain sealed aileron and a 0.15-chord plain sealed aileron on an NACA 66,2-216 airfoil. Thickening of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing section lift curve, and reduce the hinge-moment coefficients. Results regarding the section data, aileron effectiveness, aileron hinge moments, lift, pitching moment, dra… more
Date: January 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department
open access

Tests of the Northrop MX-334 Glider Airplane in the Naca Full-Scale Tunnel

Description: Report presenting tests of the Northrop MX-334 airplane in the full-scale tunnel. The results are of particular interest since the MX-334 is an all-wing glider-type airplane without a conventional fuselage or vertical surfaces. The primary purpose was to obtain sufficient data with which to determine the longitudinal and lateral stability and control characteristics of the airplane.
Date: January 1944
Creator: Brewer, Gerald W.
Partner: UNT Libraries Government Documents Department
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