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Redox Equipment Testing Report No. 4

Description: A report which covers progress on the testing of the General Engineering and Consulting Laboratory Turbine Pump No. 1 from June 16, 1948, to July 31, 1948.
Date: August 9, 1948
Creator: Cooper, V. R. & Allen, A. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Loss of Radioactivity from Barium Carbonate Samples

Description: The exchange loss of radioactivity from solid samplos of barium carbonate through the agency of carbonic acid and its ions has been investigated under a variety of conditions. It is concluded that the losses observed are greatly dependent upon the method of sample preparation, in particular the nature or any heat treatment which the sample materials undergo.
Date: January 9, 1948
Creator: Yankwich, Peter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A new device for filtering hydrofluoric acid and other strong acids. Information report

Description: During the course of a research problem involving hydrofluoric acid it became necessary to filter concentrated hydrofluoric solutions to remove various solid materials. The search for a suitable filter media finally led to the use of a commercially manufactured plastic material known as ``Sponge Teflon`` (polytetrafluoroethylone) which is produced by the DuPont Company. This material, which comes in 1/8 in. sheets, is used primarily as a gasket material in acid lines, and is impervious to all a… more
Date: July 9, 1948
Creator: Bell, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional Abstracts Pertaining to Seaplanes

Description: "About 500 additional references pertaining to hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings:GENERAL INFORMATION, HYDROSTATICS, HYDRODYNAMICS, AERODYNAMICS, OPERATION, and RESEARCH. The compilation is an extension of NACA RM No. L6I13, entitled "Abstracts Pertaining to Seaplanes," by Jerold M. Bidwell and Douglas A. King. An author index and a subject index are included" (p. 1).
Date: March 9, 1948
Creator: Bidwell, Jerold M. & King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static tests of a shrouded and an unshrouded propeller

Description: Report presenting outdoor static testing made on two high-solidity propellers of different design, one shrouded and the other unshrouded. Three shrouds were tested to determine the effects of shroud length and exit area. Results regarding the action of shroud, results and comparison of propellers, and comparison with theory are provided.
Date: February 9, 1948
Creator: Platt, Robert J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence

Description: "An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability" (p. 1).
Date: January 9, 1948
Creator: Axelson, John A. & Crown, J. Conrad
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Wing-Fuselage Combination With External Stores

Description: Report presenting an investigation of a basic wing-fuselage combination with several types of external-store installations meant to delay the advent of airplane buffet caused by external stores. Modifications for airplane design in order to minimize the effect of drag are provided. Some of the arrangements tested included the tandem-mounted arrangement, flush-mounted arrangement, store with a fan-shaped tail, and auxiliary airfoil arrangement.
Date: July 9, 1948
Creator: Silvers, H. Norman & Spreemann, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Effect of Airfoil Section Profile and Thickness Ratio on the Zero-Lift Drag of Low-Aspect-Ratio Wings at Supersonic Speeds

Description: Report discussing flight tests of airplane-like models to determine the effect of airfoil section profile and thickness ratio on the zero-lift drag of low-aspect-ratio wings at supersonic speeds. Five rectangular wings with the same aspect ratio and a variety of airfoil thicknesses were tested to determine the effect of thickness ratio.
Date: February 9, 1948
Creator: Katz, Ellis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 2: Flaps on Flat-Plate Models

Description: Memorandum presenting low-speed wind-tunnel tests made of flat-plate wings with an aspect ratio of 2.0 and their leading edges swept back 63.4 degrees. Both plain and split flaps of several plan forms were investigated to provide qualitative information as to the relative merits of these flaps. The constant-chord flap was found to be the most effective and a skewed wing-tip flap the least effective.
Date: August 9, 1948
Creator: Rose, Leonard M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning Characteristics of a 1/21-Scale Model of the Douglas AD-2W Airplane: TED No. NACA DE329

Description: Report presenting an investigation to determine the spin and recovery characteristics of a model of the Douglas AD-2W airplane, which has a large radome installation. Results indicated that the plane has satisfactory erect and inverted spin-recovery characteristics. Information about erect spins, inverted spins, and recommended recovery technique is provided.
Date: June 9, 1948
Creator: White, Richard P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 1: nacelle with offset air inlet

Description: Report presenting aerodynamic and icing investigations on a model of a turbojet-engine nacelle in order to provide icing protection for the engine, protective screen, and accessory housing by the introduction of hot gases into the inlet-air stream. Adequate ice protection was afforded when the minimum kinetic temperature in the protective screen was greater than 32 degrees Fahrenheit.
Date: July 9, 1948
Creator: Callaghan, Edmund E.; Ruggeri, Robert S. & Krebs, Richard P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Taper Ratio on the Low-Speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2.61

Description: Report discussing testing on a series of tapered swept wings under conditions simulating rolling flight. The lift, longitudinal-force, and pitching-moment characteristics for three swept wings are provided. The results indicated that a decrease in taper ratio on a swept wing caused a small decrease in damping in roll at low and moderate lift coefficients.
Date: November 9, 1948
Creator: Brewer, Jack D. & Fisher, Lewis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of high-lift devices on the low-speed stability of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow

Description: Contains results of tunnel tests to determine effects of various combinations of split flaps, slats, and nose slats on the stability characteristics of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow.
Date: November 9, 1948
Creator: Queijo, M. J. & Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61

Description: Report presenting an investigation in the stability tunnel to determine the effect of airfoil profile on symmetrical sections on the static- and yawing-stability derivatives of three untapered wings of 45 degrees sweepback. All of the wings had an aspect ratio of 2.61. Results regarding the characteristics in straight flow, yawing flow, and drag index are provided.
Date: November 9, 1948
Creator: Letko, William & Jaquet, Byron M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 2: effects of slots upon an inlet enclosing 61.5 percent of the maximum circumference of the forebody

Description: Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop duct inlet that had slots in the walls of the duct contiguous to the forebody and immediately behind the inlet. The mass flow and total-pressure recovery through the diffusor were measured during tests in which the slot length was constant and the slot width and ramp angle were varied. Results regarding mass flow and total-pressure recovery are provided.
Date: June 9, 1948
Creator: Davis, Wallace F. & Goldstein, David L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers

Description: Memorandum presenting an investigation on NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils at a range of Mach numbers and low Reynolds numbers, which indicated that the effect of increasing the trailing-edge angle was inappreciable on the Mach number for the normal-force break, to decrease the normal-force-curve slope, to reduce the effects of compressibility, and to decrease the minimum drag coefficient and to increase maximum normal-force to drag ratio.
Date: July 9, 1948
Creator: Lindsey, W. F. & Humphreys, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Wind-Tunnel Investigation at Low Speed of Various Lateral Controls on a 45 Degree Swept-Back Wing

Description: Report discussing an investigation into chord-extension controls, conventional ailerons, and spoilers on a 45 degree swept-back wing of aspect ratio 4.5 and taper ratio 0.5. Measurements of the lift, drag, pitching moments, rolling moments, and rates of roll produced by the various controls are described. The results on a semispan model and a full-span model are described.
Date: April 9, 1948
Creator: Hopkins, Edward J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Gas-turbine-engine operation with variable-area fuel nozzles

Description: Report presenting an examination of the characteristics of variable-area and fixed-area atomizing nozzles in relation to use in aircraft gas-turbine engines. A variable-area fuel nozzle and a fuel-distribution control that were used int eh experimental operation of a turbojet engine are described. Results regarding nozzle characteristics and fuel distribution, effect of atomization on engine operating characteristics, and fuel-system characteristics during engine operation are provided.
Date: July 9, 1948
Creator: Gold, Harold & Straight, David M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer 2: Effect of an Oblique Shock Wave Immediately Ahead of the Inlet

Description: Memorandum presenting an investigation of a model with a ramp that produced an oblique shock wave in front of an annular duct inlet, which was tested at Mach numbers between 1.36 and 2.01 to determine the effect of reducing the entrance Mach number on the total-pressure recovery after diffusion. The results showed that the maximum total-pressure recovery of the model investigated was considerably improved through the addition of a ramp.
Date: August 9, 1948
Creator: Brajnikoff, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The calculation of downwash behind supersonic wings with an application to triangular plan forms

Description: A method is developed consistent with the assumptions of small perturbation theory which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The equivalence in subsonic and supersonic flow of the downwash at infinity corresponding to a given load distribution is proved.
Date: November 9, 1948
Creator: Lomax, Harvard; Sluder, Loma & Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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