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Drag Measurements of Symmetrical Circular-Arc and NACA 65-009 Rectangular Airfoils Having an Aspect Ratio of 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing testing to determine the drag characteristics at zero lift of a wing with a circular-arc airfoil section with a maximum thickness of 9 percent chord. The results were compared to previous testing on an NACA 65-009 airfoil. It was found that the NACA airfoil had lower drag coefficients than the circular-arc airfoil tested in this experiment.
Date: March 7, 1947
Creator: Alexander, Sidney R.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Description: Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date: March 11, 1947
Creator: Bartlett, Walter A., Jr. & Goral, Edwin B.
Partner: UNT Libraries Government Documents Department
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A Simplified Method of Elastic-Stability Analysis for Thin Cylindrical Shells

Description: "This paper develops a new method for determining the buckling stresses of cylindrical shells under various loading conditions. In part I, the equation for the equilibrium of cylindrical shells introduced by Donnell in NACA report no. 479 to find the critical stresses of cylinders in torsion is applied to find critical stresses for cylinders with simply supported edges under other loading conditions. In part II, a modified form of Donnell's equation for the equilibrium of thin cylindrical shell… more
Date: March 20, 1947
Creator: Batdorf, S. B.
Partner: UNT Libraries Government Documents Department
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Critical Combinations of Shear and Direct Stress for Simply Supported Rectangular Flat Plates

Description: Note presenting an investigation of the buckling of a simply supported rectangular flat plate under combinations of shear and direct stress by means of an energy method. The critical combinations of stress for several length-width ratios were determined to an accuracy of about 1 percent in conjunction with a modified matrix iteration method. Results regarding the shear and longitudinal stress and shear and transverse stress are provided.
Date: March 1947
Creator: Batdorf, S. B. & Stein, Manuel
Partner: UNT Libraries Government Documents Department
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Critical Stress of Thin-Walled Cylinders in Axial Compression

Description: Empirical design curves are presented for the critical stress of thin-wall cylinders loaded in axial compression. These curves are plotted in terms of the nondimensional parameters of small-deflection theory and are compared with theoretical curves derived for the buckling of cylinders with simply supported and clamped edges. An empirical equation is given for the buckling of cylinders having a length-radius ratio greater than about 0.75.
Date: March 20, 1947
Creator: Batdorf, S. B.; Schildcrout, Murry & Stein, Manuel
Partner: UNT Libraries Government Documents Department
open access

Wake measurements behind a wing section of a fighter airplane in fast dives

Description: Report presenting wake measurements made in a vertical plane behind a wind section of a fighter airplane for a range of Mach numbers up to 0.78. The critical Mach number of each wing section was exceeded by 0.05 before large increases in the profile-drag coefficient occurred.
Date: March 1947
Creator: Beeler, De E. & Gerard, George
Partner: UNT Libraries Government Documents Department
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Effect of Exhaust Pressure on the Performance of an 18-Cylinder Air-Cooled Radial Engine with a Valve Overlap of 40 Degrees

Description: Note presenting an investigation to determine the effect of exhaust pressure on the performance of an 18-cylinder air-cooled radial engine equipped with a conventional exhaust collector ring. The engine power increased at a diminishing rate as exhaust pressure decreased.
Date: March 1947
Creator: Boman, David S.; Nagey, Tibor F. & Doyle, Ronald B.
Partner: UNT Libraries Government Documents Department
open access

The Maintenance of Animals Containing Radioactive Materials

Description: Abstract: In the Biology Division, the maintenance of animals containing radioactive materials posed many problems. In addition to routine care of the animals, protection had to be provided for the personnel who worked with the contaminated animals. Frequent air changed in the room in which the animals were caged were necessary: farm workers were required to wear masks; animal cages were checked regularly for radiation; acid was used on the sawdust in the excrete pens; and a new, more efficient… more
Date: March 24, 1947
Creator: Britton, Paul; Lear, Patricia; Prosser, C. Ladd (Clifford Ladd), 1907-2002 & Tyree, Ella
Partner: UNT Libraries Government Documents Department
open access

Wing Pressure-Distribution Measurements Up to 0.866 Mach Number in Flight on a Jet-Propelled Airplane

Description: Report presenting flight testing to determine scale and compressibility effects on the pressure distributions over a wing with an NACA low-drag profile. No compressibility effects on spanwise wing loading were noted below Mach number 0.75, but above that number, an inboard lateral shift of load occurred that is primarily due to the upfloating of the ailerons.
Date: March 1947
Creator: Brown, Harvey H. & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department
open access

Knock-Limited Performance of Triptane and 28-R Fuel Blends as Affected by Changes in Compression Ratio and in Engine Operating Variables

Description: From Summary: "A knock-limited performance investigation was conducted on blends of triptane and 28-P fuel with a 12-cylinder, V-type, liquid-cooled aircraft engine of 1710-cubic-inch displacement at three compression ratios: 6.65, 7.93, and 9.68. At each compression ratio, the effect of changes in temperature of the inlet air to the auxiliary-stage supercharger and in fuel-air ratio were investigated at engine speeds of 2280 and. 3000 rpm. The results show that knock-limited engine performance… more
Date: March 11, 1947
Creator: Brun, Rinaldo J.; Feder, Melvin S. & Fisher, William F.
Partner: UNT Libraries Government Documents Department
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Experimental and theoretical studies of surging in continuous-flow compressors

Description: Report describing experiments to determine the conditions that cause surging in compressors and to determine the effect of various installations and operating conditions on the character of the velocity and pressure variations occurring during surging. Surging was found to be a periodic variation of pressures and velocities that may occur when the slope of the compressor characteristic curve is positive.
Date: March 1947
Creator: Bullock, Robert O.; Wilcox, Ward W. & Moses, Jason J.
Partner: UNT Libraries Government Documents Department
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Infinitesimal Conical Supersonic Flow

Description: The calculation of infinitesimal conical supersonic flow has been applied first to the simplest examples that have also been calculated in another way. Except for the discovery of a miscalculation in an older report, there was found the expected conformity. The new method of calculation is limited more definitely to the conical case.
Date: March 1947
Creator: Busemann, Adolf
Partner: UNT Libraries Government Documents Department
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Progress Report for the Month of March, 1947 : Contract No. W-38-094-eng-27

Description: This report for March, 1947 describes progress regarding chemical and spectrographic analysis, chemical work, physical methods of analysis, and ore dressing and pyrometallurgical studies,
Date: March 31, 1947
Creator: Center, E. J.; Nelson, H. R.; Pray, H. A.; Richardson, A. C. & Sullivan, J. D.
Partner: UNT Libraries Government Documents Department
open access

Effect of combustor-inlet conditions on performance of an annular turbojet combustor

Description: From Summary: "The combustion performance, and particularly the phenomenon of altitude operational limits, was studied by operating the annular combustor of a turbojet engine over a range of conditions of air flow, inlet pressure, inlet temperature, and fuel flow. Information was obtained on the combustion efficiencies, the effect on combustion of inlet variables, the altitude operational limits with two different fuels, the pressure losses in the combustor, the temperature and velocity profile… more
Date: March 21, 1947
Creator: Childs, J. Howard; McCafferty, Richard J. & Surine, Oakley W.
Partner: UNT Libraries Government Documents Department
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A Preliminary Theoretical Study of Aerodynamic Instability of a Two-Blade Helicopter Rotor

Description: Report presenting numerical results of flutter calculations for a two-blade helicopter using a see-saw-type rotor. The stability condition for oscillatory motion is expressed in terms of a small number of composite parameters that are evaluated from moments of inertia, angle settings, and aerodynamic parameters of a blade. The analysis indicated that a see-saw rotor with a coning angle is more unstable than an airplane wing with the same parameters.
Date: March 18, 1947
Creator: Coleman, Robert P. & Stempin, Carl W.
Partner: UNT Libraries Government Documents Department
open access

Effect of Reflex Camber on the Aerodynamic Characteristics of a Highly Tapered Moderately Swept-Back Wing at Reynolds Numbers Up to 8,000,000

Description: Report presenting testing at Reynolds numbers up to 8,000,000 to determine the effectiveness of a reflex-cambered mean line in shifting the low-drag range of a sweptback wing without affecting the longitudinal stability. Two models were tested, one with symmetrical airfoil sections and one with a reflex-cambered mean line. Results regarding the effect of camber, roughness, and variation of aerodynamic characteristics with Reynolds number are provided.
Date: March 1947
Creator: Conner, D. William
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Description: From Summary: "A study has been made of the performance of the induction and the exhaust systems on the XR60 power-plant installation as part of an investigation conducted in the Cleveland altitude wind tunnel. Altitude flight conditions from 5000 to 30,000 feet were simulated for a range of engine powers from 750 to 3000 brake horsepower."
Date: March 28, 1947
Creator: Dupree, David T. & Hawkins, W. Kent
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Stress Distribution Around Reinforced Circular Cut-Outs in Skin Stringer Panels Under Axial Loads

Description: Note presenting results of strain surveys around four reinforced circular cut-outs successively made in an axially loaded skin-stringer tension panel. Curves are presented which show the distribution of stringer and shear stresses in the panel and bending stresses in the reinforcing rings.
Date: March 1947
Creator: Farb, Daniel
Partner: UNT Libraries Government Documents Department
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Ditching Tests of a 1/18-Scale Model of the Navy XP4M-1 Airplane in Langley Tank No. 2 and on an Outdoor Catapult, TED No. NACA 2362

Description: From Summary: "Tests with a dynamically similar model of the Navy XP4M-1 airplane were made to determine the best way to land the airplane in calm and rough water, to determine its probable ditching performance, and to determine practicable modifications which could be incorporated in the design of the airplane that would improve its ditching characteristics. The results were obtained by making visual observations, by recording longitudinal decelerations ,and by taking motion pictures of the la… more
Date: March 10, 1947
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Partner: UNT Libraries Government Documents Department
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Ditching Tests with a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail

Description: "Tests were made with a 1/16 size dynamically similar model of the Navy XP2V-1 airplane to study its performance when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated" (p. 1).
Date: March 14, 1947
Creator: Fisher, Lloyd J. & Tarshis, Robert P.
Partner: UNT Libraries Government Documents Department
open access

The Recovery of C$Sup 14$ From Irradiated Beryllium Nitride

Description: Methods for the recovery of C/sup 14/ from neutron-irradiated Re/sub 3/N/ sub 2/, based on solution in acid and alkali. are outlined. (C.J.G.)
Date: March 1, 1947
Creator: Fries, B. A.
Partner: UNT Libraries Government Documents Department
open access

The Recovery of C14 From Irradiated Beryllium Nitride

Description: Both acid and alkaline dissolutions of Be/sub 3/N/sub 2/ were carried The recommended alkaline dissolution procedure is outlined. (M.H.R.)
Date: March 1, 1947
Creator: Fries, B. A.
Partner: UNT Libraries Government Documents Department
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