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Thermodynamic Diagrams for Sodium

Description: From abstract: This paper presents temperature-entropy and Mollier charts for sodium, and describes briefly the method used for their construction, based upon data from the literature.
Date: July 13, 1950
Creator: Inatomi, T. H. & Parrish, W. C.
Partner: UNT Libraries Government Documents Department
open access

Effects of Obstructions in Compressor Inlet on Blade Vibration in 10-Stage Axial-Flow Compressor

Description: Report presenting a blade-vibration survey that was conducted during normal operation of a 10-stage axial-flow compressor powered by part of a complete jet engine. Strain-gage records were obtained from all stages during acceleration, deceleration, and constant-speed runs. Results regarding the inlet disturbances and damping characteristics are provided.
Date: February 13, 1950
Creator: Meyer, André J., Jr.; Calvert, Howard F. & Morse, C. Robert
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of porous walls as a means of reducing tunnel boundary effects at low-supersonic Mach numbers

Description: Report presenting the use of porous-walled tunnels at supersonic Mach numbers as a means of avoiding reflection of a stream disturbance extending to the walls. Results from analysis and an experiment with a 4 degree wedge at a Mach number of 1.2 are provided.
Date: September 13, 1950
Creator: Nelson, William J. & Bloetscher, Frederick
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Propeller Efficiency at High Subsonic Flight Speeds near Mach Number Unity

Description: From Introduction: "Tests have recently been conducted in the Langley 8-foot high-speed tunnel (reference 1) to study the effects of changes in operating advance ratio, blade plan form, blade-section thickness, section camber, and other variables on the on the propeller characteristics in the transonic-speed range. The method in reference 2, which evaluated the profile drag losses and the induced losses seperately, is followed in this paper. The method as presented offers the general prediction… more
Date: February 13, 1950
Creator: Gilman, Jean, Jr.; Crigler, John L. & McLean, F. Edward
Partner: UNT Libraries Government Documents Department
open access

Chordwise and Spanwise Loadings Measured at a Large Triangular Wing Having an Aspect Ratio of 2 and a Thin, Subsonic-Type Airfoil Section

Description: Memorandum presenting pressure-distribution and force data at various angles of attack of a triangular wing of aspect ratio 2 and having an NACA 0005 modified section. The wing had a plain, constant-chord, trailing-edge flap which was deflected 0 and 10 degrees. Results regarding the gross force characteristics of the wing, including lift, drag, pitching-moment, and flap hinge-moment coefficients are provided.
Date: March 13, 1950
Creator: Graham, David
Partner: UNT Libraries Government Documents Department
open access

Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers

Description: Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date: April 13, 1950
Creator: Gabriel, David S.; Dowman, Harry W. & Jones, William L.
Partner: UNT Libraries Government Documents Department
open access

Investigation of ignition characteristics of AN-F-32 and two AN-F-58a fuels in single can-type turbojet combustor

Description: Ignition characteristics of AN-F-32 and two AN-F-58a fuels were studied in a single can-type turbojet combustor under air-flow conditions representing engine speeds of 1600, 2500, and 4000 rpm, altitudes from sea level to 30,000 feet, ambient temperatures at sea level from 90 degrees to minus 36 degrees F, and flight Mach numbers of 0 and 0.6. Critical fuel-flow rates for ignition increased with increase in preignition engine speed, with increase in altitude, or with decrease in sea-level ambie… more
Date: October 13, 1950
Creator: Rayle, Warren D. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Dynamic Longitudinal Stability of Two Equal Size Models Coupled in Tandem with a Single Joint: Preliminary Model Flight Tests

Description: Report presenting an investigation in the free-flight tunnel to study the dynamic longitudinal stability of equal-size models coupled in tandem with a single joint providing freedom in pitch. Results regarding the characteristics of the model motions, effect of elevator gearing ratio, effect of weight ratio, and effect of static stability of the front model are provided.
Date: November 13, 1950
Creator: Shanks, Robert E. & Grana, David C.
Partner: UNT Libraries Government Documents Department
open access

Preliminary analysis of three cycles for nuclear propulsion of aircraft

Description: A preliminary study was made of the feasibility of three cycles for nuclear propulsion of aircraft: a direct-air-turbojet, a binary liquid-metal turbojet, and a helium compressor jet. All three cycles appeared feasible for flight at a Mach number of 0.9 and altitudes up to 50,000 feet; the liquid-metal cycle appeared feasible for flight at a Mach number of 1.5. The air and helium cycles resulted in heavier aircraft than did the liquid-metal cycle, particularly at a Mach number of 1.5. The relat… more
Date: October 13, 1950
Creator: Humble, L. V.; Wachtl, W. W. & Doyle, R. B.
Partner: UNT Libraries Government Documents Department
open access

Investigation of effects of inlet-air velocity distortion on performance of turbojet engine

Description: To determine effect of nonuniform inlet-air velocities, a full scale, axial-flow turbojet engine was investigated in Lewis altitude wind tunnel at altitudes from 20,000 to 50,000 feet, 0.21 flight Mach number and corrected engine speeds from 77.3 percent of rated speed to rated speed. Total-pressure variations as large as 103 pounds per square foot in radial direction and 90 pounds per square foot in circumferential direction at 30,000 feet were obtained. With the distortions investigated, net … more
Date: September 13, 1950
Creator: Conrad, E. William & Sobolewski, Adam E.
Partner: UNT Libraries Government Documents Department
open access

Factors in selecting fuels for gas-turbine powered aircraft

Description: "This report briefly summarizes some of the available information on fuels for gas-turbine powered aircraft. The effects of fuel volatility and composition on the range, reliability, and safety of aircraft are discussed. Availability is briefly considered for fuels at various volatility levels" (p. 1).
Date: November 13, 1950
Creator: Gibbons, Louis C.
Partner: UNT Libraries Government Documents Department
open access

Ability of Pilots to Control Simulated Short-Period Yawing Oscillations

Description: Report discussing an investigation into the ability of human pilots to control short-period yawing oscillations using a yaw simulating device. The ability to control the oscillations was determined to be a function of period, control effectiveness, and inherent damping. Pilot control effectiveness was found to improve with practice.
Date: November 13, 1950
Creator: Phillips, William H. & Cheatham, Donald C.
Partner: UNT Libraries Government Documents Department
open access

The Time Lag Between Flap Deflection and Force Development at a Mach Number of 4

Description: Report presenting an investigation of the time lag between flap deflection and force development on a rectangular wing with a 9-percent-thick symmetrical circular-arc profile with a full-span 30-percent-chord flap. This was performed in order to determine further information about the rapidity of response for a supersonic missile after a given flap deflection due to the potential time lag between the deflection of the controls surfaces and the development of aerodynamic forces.
Date: February 13, 1950
Creator: Lindsey, Walter F. & Ulmann, Edward F.
Partner: UNT Libraries Government Documents Department
open access

Summary report of results obtained during demonstration tests of the Northrop X-4 airplanes

Description: Report presenting results during demonstration flight tests of the Northrop X-4 No. 1 and No. 2 airplanes. Results regarding the static and dynamic longitudinal- and lateral-stability characteristics, the stalling characteristics, and the buffet boundary.
Date: December 13, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - trailing-edge flaps deflected

Description: Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, trailing-edge flaps using wind-tunnel testing of a semispan model. The trailing-edge flap was generally effective in changing the lift coefficient at each angle of attack and Mach number of the investigation. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteris… more
Date: December 13, 1950
Creator: Stivers, Louis S., Jr. & Malick, Alexander W.
Partner: UNT Libraries Government Documents Department
open access

Combustion efficiencies in hydrocarbon-air systems at reduced pressures

Description: Report presenting results obtained with quiescent fuel-air mixtures and with small diffusion flames, which indicate that combustion efficiencies close to 100 percent were obtained at pressure much lower than those found in turbojet combustors at altitudes of 60,000 feet.
Date: September 13, 1950
Creator: Hibbard, Robert R.; Drell, Isadore L.; Metzler, Allen J. & Spakowski, Adolph E.
Partner: UNT Libraries Government Documents Department
open access

Method for calculating lift distributions for unswept wings with flaps or ailerons by use of nonlinear section lift data

Description: A method is presented which allows the use of nonlinear section lift data in the calculation of the spanwise lift distribution of unswept wings with flaps or ailerons. This method is based upon lifting line theory and is an extension to the method described in NACA rep. 865. The mathematical treatment of the discontinuity in absolute angle of attack at the end of the flap or aileron involves the use of a correction factor which accounts for the inability of a limited trigonometric series to rep… more
Date: November 13, 1950
Creator: Sivells, James C. & Westrick, Gertrude C.
Partner: UNT Libraries Government Documents Department
open access

Method of analysis for compressible flow through mixed-flow centrifugal impellers of arbitrary design

Description: A method is presented for analysis of the compressible flow between the hub and the shroud of mixed-flow impellers of arbitrary design. Axial symmetry was assumed, but the forces in the meridional (hub to shroud) plane, which are derived from tangential pressure gradients, were taken into account. The method was applied to an experimental mixed-flow impeller. The analysis of the flow in the meridional plane of the impeller showed that the rotational forces, the blade curvature, and the hub-shro… more
Date: April 13, 1950
Creator: Hamrick, Joseph T.; Ginsburg, Ambrose & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department
open access

Review of DR water plant design for possible expansion

Description: A study of the design of the DR Water Plant made for the purpose of estimating the feasibility of effecting an expansion of capacity has shown the following: (1) The Charles T. Main Company design has incorporated spare spaces and other provisions to permit a relatively simple increase in capacity to 42,000 GPM without undue additional design or procurement being required. (2) An increase in capacity to 44,000 GPM would require considerable re-design of the 183-DR, 190-DR and interconnecting pi… more
Date: February 13, 1950
Partner: UNT Libraries Government Documents Department
open access

Processing of special low-level material, T Plant only

Description: This report discusses the processing of 55 MWD per ton metal, at the Hanford Works` T-Plant in December, 1950.
Date: December 13, 1950
Creator: Mobley, W. N.
Partner: UNT Libraries Government Documents Department
open access

Preparation of Anhydrous Vanadium Trifluoride

Description: Report discussing a procedure for the preparation of anhydrous vanadium trifluoride. From abstract: "By selecting proper operating conditions and equipment, a method of preparation was devised such that anhydrous vanadium trifluoride of high purity was produced reliably in five pound batches." The method of preparation involves manipulating the starting material, vanadium pentoxide.
Date: March 13, 1950
Creator: Mackey, T. S. & Johnsson, K. O.
Partner: UNT Libraries Government Documents Department
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