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Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
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Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Partner: UNT Libraries Government Documents Department
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Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Partner: UNT Libraries Government Documents Department
open access

Analysis of Bulk Shielding Facility Neutron Dosimeter Data

Description: Technical report calculating "effective removal cross sections" for Pb, Fe and O from measurements of fast neutron does in the water surrounding the BSF reactor. The values for Pb and Fe agree quite well with those previously determined from Lid tank data, whereas that for O is somewhat lower. [From Abstract]
Date: July 17, 1952
Creator: Podgor, S.
Partner: UNT Libraries Government Documents Department
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An Analytical Study of the Comparative Performance of Four Air-Induction Systems for Turbojet-Powered Airplanes Designed to Operate at Mach Numbers Up to 1.5

Description: Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.
Date: June 17, 1952
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department
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Anodization of process tubes

Description: This report discusses the presence of corrosion products upon aluminum process tubes removed from wet portions of F Pile which led to the suspicion that the tubes might be corroding at an accelerated rate because of water entrapped in the channels between the tubes and the graphite blocks. Corrosion was especially noted on those tubes that were tightly stuck within the blocks. Analysis of the corrosion products showed that the major constituent was a hydrated aluminum oxide, containing iron oxi… more
Date: September 17, 1952
Creator: Pitzer, E. C.
Partner: UNT Libraries Government Documents Department
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A Cement Base for the Hot Filament Mass Spectrometer Source

Description: The following document is meant to inform the reader on the makings of a cement base for the hot filament mass spectrometer source as part of a publication in the review of scientific instruments, "Laboratory and Shop Notes".
Date: January 17, 1952
Creator: Hand, John E.
Partner: UNT Libraries Government Documents Department
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Combustion efficiency of homogeneous fuel-air mixtures in a 5-inch ram-jet-type combustor

Description: Report presenting combustion-efficiency data for a 5-inch-diameter combustor employing a straight V-gutter flame holder and a simple cone flame holder. The data covers a range of inlet static pressures, temperatures, and velocities for four fuels. The majority of the data indicated that the combustion efficiency was relatively insensitive to fuel-air ratio over the range of fuel-air ratios investigated.
Date: November 17, 1952
Creator: Reynolds, Thaine W. & Ingebo, Robert D.
Partner: UNT Libraries Government Documents Department
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Comparison of Locked-Rotor and Windmilling Drag Characteristics of an Axial-Flow-Compressor Type Turbojet Engine

Description: The internal drag of an axial-flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8.
Date: January 17, 1952
Creator: Vincent, K. R.; Huntley, S. C. & Wilsted, H. D.
Partner: UNT Libraries Government Documents Department
open access

Decay Tables for the Natural Radioactive Series III. Thorium (4n) Series

Description: The third in this series of reports presents tables dealing with the growth and decay of members of the thorium family of naturally occurring radioisotopes. The general equations and approximations used in computing these tables are the same as those presented in Part I of the series.
Date: November 17, 1952
Creator: Kirby, H. W.
Partner: UNT Libraries Government Documents Department
open access

Design basis for proposed separations facility, for use in preliminary project proposal

Description: Members of the Working Committees for RDA DC-4 and RDA DC-7 (KE and KW Reactors) have reviewed and approved the design basis being used for the preparation of the 200 Area portion of the Program X preliminary project proposal. This design basis includes the following: plant capacity of 275 tons per month, average flow rate; the basic chemical process used will be the Purex process; the plant will be located in the Southeast Quadrant of the 200 East Area; the plant will contain a double line of … more
Date: March 17, 1952
Partner: UNT Libraries Government Documents Department
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The dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Description: From Summary: "The longitudinal and lateral-directional dynamic-response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements are presented and compared with predictions based on theoretical studies and wind-tunnel data. Flights were made at an altitude of 35,000 feet covering the Mach number range of 0.50 to 1.04. A limited amount of lateral-directional data were also obtained at 10,000 feet. The flight consisted essentially of recording transient… more
Date: September 17, 1952
Creator: Triplett, William C.; Brown, Stuart C. & Smith, G. Allan
Partner: UNT Libraries Government Documents Department
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Effect of inlet air and fuel parameters on smoking characteristics of a single tubular turbojet engine combustor

Description: Report presenting an investigation to determine the effect of systematic variations in inlet-air and fuel parameters on the smoking characteristics of a single tubular turbojet-engine combustor. The most pronounced effect on smoke was observed with increase in inlet-air pressure which produced large increases in smoke concentration. Results regarding the reproducibility of smoke measurements, effect of fuel-air ratio and inlet-air parameters on smoke density, effect of fuel parameters on smoke … more
Date: April 17, 1952
Creator: Butze, Helmut F.
Partner: UNT Libraries Government Documents Department
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Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. 4 - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages

Description: "The performance of a 16-stage axial-flow compressor, in which two modifications of unloaded inlet stages were combined with loaded exit stages, has been determined. In the first modification the exit stages were loaded by decreasing the twelfth through fifteenth stage stator angles 3 deg. as compared with the blade angles in the original compressor, and the inlet stages were unloaded by increasing the blade angles the following amounts: guide vanes and first-stage stator, 6 deg; second- and th… more
Date: March 17, 1952
Creator: Hatch, James E. & Medeiros, Arthur A.
Partner: UNT Libraries Government Documents Department
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Effects of finite span on the section characteristics of two 45 degree swept-back wings of aspect ratio 6

Description: Report presenting a study of the finite-span effects on the local loading characteristics of two sweptback wings at low speed in order to provide some information about the usefulness of two-dimensional section data and span-loading theory for determining the section characteristics of a swept wing. At low values of lift coefficient, the finite-span effects were restricted to regions of the wing close to the root and tip. Results regarding the local pressure-distribution comparisons, local lift… more
Date: March 17, 1952
Creator: Hunton, Lynn W.
Partner: UNT Libraries Government Documents Department
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Effects of High Intensity Radiant Energy on Skin: [Part] 1. Type of Energy and Its Relation to Energy Delivery Rate

Description: Abstract: Burn lesions were produced by radiant energy, 3100 A to 22000 A, on depilated rat skin. The gross and microscopic pathological changes so caused are described and correlated with the amounts of incident energy and the rate of energy delivery. Within the limits studied, 0.2 to 64 cal./cm.2/sec. and 0.1 to 8.0 seconds, it was found that increasing the rate of energy delivery lowered the amount of energy required to produce a specified degree of tissue injury. The tissue changes were in … more
Date: March 17, 1952
Creator: Sheline, Glenn E.; Alpen, Edward L.; Kuhl, P. R. & Ahokas, A.
Partner: UNT Libraries Government Documents Department
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Effects of wing elasticity on the aerodynamic characteristics of a 45 degree sweptback-wing-fuselage combination measured in the Langley 8-foot transonic tunnel

Description: Report presenting testing of a wing-fuselage configuration with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections in aluminum and steel at a range of Mach numbers and angles of attack to determine effects of wing elasticity. Results regarding the relative effects of bending and torsion, wing-tip twist, aerodynamic characteristics, and some theoretical considerations are provided.
Date: September 17, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of a conservatively designed turbine at four rotor-blade solidities

Description: Report presenting a program to determine limiting values of the aerodynamic parameters used in turbine design, which includes a study of several turbine designs suitable for application in current aircraft power plants. In this first report, the performance of a single-stage turbine of conservative design was studied for the purpose of establishing a basis for the comparison of turbine performance of less conservative designs.
Date: July 17, 1952
Creator: Heller, Jack A.; Whitney, Rose L. & Cavicchi, Richard H.
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98

Description: Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. The basic body shape was a 10-caliber tangent ogive nose with a cylindrical afterbody, while other shapes tested had either a blunt-nosed profile or a boat-tailed afterbody. Results regarding the variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shape, vari… more
Date: September 17, 1952
Creator: Reller, John O., Jr. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department
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Flight Determination of the Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Northrop MX-775A Missile at Low Lift Coefficients and Mach Numbers From 0.89 to 1.34

Description: Report presenting a flight investigation to determine the longitudinal stability of a scale model of the Northrop MX-775A missile at low lift coefficients through a range of Mach numbers. Results regarding the trimmed flight and model pitching are provided.
Date: September 17, 1952
Creator: Gillespie, Warren, Jr. & Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
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Force Tests of Three Thin Wings of Moderately Low Aspect Ratio at High Subsonic Mach Numbers

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of leading-edge shape and section profile on the aerodynamic characteristics of two thin wings of aspect ratio 4. Lift, drag, and pitching-moment data are presented for a range of angles of attack and Mach numbers. Information about a third wing with an aspect ratio of 3, a taper ratio of 0.4, and a 4.5-percent-thick modified-hexagonal section are also provided.
Date: October 17, 1952
Creator: Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department
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Free-spinning-tunnel investigation of a 1/30-scale model of the Grumman XS2F-1 airplane: TED No. NACA DE 366

Description: Report presenting an investigation of a 1/30-scale model of the Grumman XS2F-1 airplane in the 20-foot free-spinning tunnel to determine the erect spin and recovery characteristics of the model in the design flight condition and with the center of gravity at 30 percent of the mean aerodynamic chord. Results regarding the erect spins, inverted spins, spin-recovery parachutes, influence of power, control forces, landing condition, and recommended recovery technique are provided.
Date: September 17, 1952
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department
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Hydrogen Peroxide Analysis and Decomposition in Chromate Solutions

Description: Abstract: "A novel procedure employing ion exchange resins was developed to separate chromate ions from hydrogen peroxide, permitting, permitting the subsequent analysis of peroxide to determine its decomposition in sodium chromate solutions. At high pH's, peroxide was absorbed anionically on the ion exchange resins along with chromate. By selecting a resin which would be effective at nearly neutral conditions, chromate was satisfactorily separated from peroxide. It was found that the rate of p… more
Date: March 17, 1952
Creator: Rynasiewicz, Joseph & Ryan, J. W.
Partner: UNT Libraries Government Documents Department
open access

Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds

Description: Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.
Date: October 17, 1952
Creator: Paradiso, Nicholas J.
Partner: UNT Libraries Government Documents Department
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