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- Ames Project, Chemical Research - General Chemistry, Report for the Period of April 10 to May 10, 1944
- Technical report. Areas covered are properties of uranium halides, properties of uranium nitrides, and hydride formation at high pressure.
- An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship
- From Summary: "The heat losses from the envelope surface of a U.S. Navy K-type airship are evaluated to determine if the use of heat is a feasible means of preventing ice and snow accumulations on lighter-than-air craft during flight and when moored uncovered. Consideration is given to heat losses in clear air (no liquid water present in the atmosphere) and in probable conditions of icing and snow. The results of the analysis indicate that the amount of heat required in flight to raise the surface temperature of the entire envelope to the extent considered adequate for ice protection, based on experience with tests of heavier-than-air craft, is very large."
- The Biologic Effects of Radiation ; Training Program Lecture Notes
- The following report provides data taken from investigations on radiation and the different biologic effects on it.
- Calibration Tests of a German Log Rodmeter
- A German log rodmeter of the pitot static type was calibrated in Langley tank no. 1 at speeds up to 34 knots and angles of yaw from 0 deg to plus or minus 10 3/4 degrees. The dynamic head approximated the theoretical head at 0 degrees yaw but decreased as the yaw was increased. The static head was negative and in general became more negative with increasing speed and yaw. Cavitation occurred at speeds above 31 knots at 0 deg yaw and 21 knots at 10 3/4 deg yaw.
- Capture of Fast Neutrons by Pb208
- From abstract: "Comparison of the activity produced by fast neutrons on lead with other activations corroborates the assignment of the 3.2 hr. activity as Pb209, and the assignment of the reaction as capture of fast neutrons. Two different measurements show that the neutrons captured have energies greater than 100 KEV. This average capture cross section for primary neutrons from 7.5 MEV deuterons on a thick target of beryllium is measured as 10[^]-27 ca[^]2."
- Charts of Compressibility Factors and Charts Showing Quantities Delivered by Commercial Cylinders for Hydrogen, Nitrogen, and Oxygen
- Two charts are given for each of the gases hydrogen, nitrogen, and oxygen. The first gives directly the number of standard cubic feet of the gas which a cylinder will deliver. The second chart gives values of the compressibility factor and of the density.
- Comparison of Theoretical and Experimental Heat-Transfer Characteristics of Bodies of Revolution at Supersonic Speeds
- "An investigation of the three important factors that determine convective heat-transfer characteristics at supersonic speeds, location boundary-layer transition, recovery factor, and heat-transfer parameter has been performed at Mach numbers from 1.49 to 1.18. The bodies of revolution that were tested had, in most cases, laminar boundary layers, and the test results have been compared with available theory. Boundary-layer transition was found to be affected by heat transfer" (p. 1301).
- Control during starting of gas-turbine engines
- Report presenting an investigation of the variables pertinent to the control of gas temperatures of gas-turbine engines during starting conducted by obtaining time records of the variables involved during actual starting conditions. Poor control of gas temperatures during starting was found to be caused by an accumulation of fuel in the engine before ignition and excessive fuel-flow rates at the time of ignition.
- Control requirements and control parameters for a ram jet with variable-area exhaust nozzle
- Report presenting control requirements and parameters for a ram jet with a variable-area exhaust nozzle, which have been analyzed from calculated performance charts covering flight Mach numbers from 0.6 to 3.0 and altitudes from sea level to 30,000 feet. Requirements for maximum efficiency, safe and stable operation, maximum range of thrust at a given flight Mach number, and control of fuel flow are discussed and control parameters are selected.
- The Effect of Rear Chine Strips on the Take-Off Characteristics of a High-Speed Airplane Fitted With NACA Hydro-Skis
- "Results are presented from tank take-off tests of a dynamic model of a hypothetical high-speed airplane fitted with NACA hydro-skis and having the transverse curvature of the lower rear portion of the fuselage broken by small longitudinal chine strips. For the configuration tested, both trim and resistance were considerably reduced by the addition of the strips from the speed at which the ski emerged to the speed at which the rear of the fuselage came clear of the water. The results indicate that fuselage shape has a large effect on the take-off characteristics for a hydro-ski configuration in which the rear of the fuselage acts as a planing surface" (p. 1).
- The Effect of Temperature on the Distribution of Nitric Acid Between Dibutyl Carbitol and Aqueous Solutions of Copper Nitrate
- This report follows a test made to determine the effect of temperature on the distribution of nitric acid between "carbitol" and gunk, extracting a number of samples of aqueous copper nitrate with samples of "carbitol" of various acidities. The data obtained is covered in Table 1.
- Effects of Total Body Z Irradiation of Rats. Part I, Lethal Action of Single, Paired, and Periodic Doses
- Abstract: Exposure of Sprague Dawley white rats to single doses of 900 kvp X radiation demonstrated a medium lethal dose of 600 r which was not markedly dependent upon sex, weight, or, in the case of females, stage of the estrous cycle at the time of irradiation. Deaths within 30 days were most frequent between the fourth and eighth, and between the tenth and fifteenth post- irradiation days, indicating the existence of at least two processes leading to death in the "acute" period.
- Examination made for Mr. Marc Jenkins of a property in the White Signal mining district, Grant County, New Mexico
- A report made of the examination of a prospect in the White Signal mining district of Grant County, New Mexico.
- Free-Flight Investigation of the Rolling Effectiveness of a Wing-Spoiler Arrangement at High Subsonic, Transonic, and Supersonic Speeds
- Report presenting an investigation of the rolling effectiveness of a wing-spoiler arrangement using a rocket-propelled test vehicle in free flight. The configuration investigated in the report is likely not optimum and indicates a need for further exploration.
- Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the Chance Vought XF5U-1 Airplane, TED No. NACA 2349
- "Spin tests of a 1/16-scale model of the Chance Vought XF5U-1 airplane have been performed in the Langley 20-foot free-spinning tunnel. The effect of control position and movement upon the erect and inverted spin and recovery characteristics as well as the effects of propellers, of stability flaps, and of various revisions to the design configuration have been determined for the normal fighter loading. The investigation also included spin recovery parachute, tumbling, and pilot-escape tests" (p. 1).
- Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the North American XP-86 Airplane
- "A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the North American XP-86 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the design gross weight loading. The long-range loading was also investigated and the effects of extending slats and dive flaps were determined" (p. 1).
- Freezing Point Data for UNH-H₂O-HNO₃ Systems
- The following report follows a series of experiments on the freezing points of 25 UN-H2O-HNO3 solutions.
- Further Critical Experiments on a Small Reactor of Enriched U-235 with Al-Hâ‚‚O Moderator and Beryllium Reflector
- From introduction: "The purpose of the present report is to describe briefly certain improvements that have been made in the experimental facilities and to present the results of further measurements on critical masses and spatial neutron flax distributions in Be reflected reactors having square and thin slab geometries."
- Hydrodynamic impact of a system with a single elastic mode I : theory and generalized solution with an application to an elastic airframe
- Solutions of impact of a rigid prismatic float connected by a massless spring to a rigid upper mass are presented. The solutions are based on hydrodynamic theory which has been experimentally confirmed for a rigid structure. Equations are given for defining the spring constant and the ratio of the sprung mass to the lower mass so that the two-mass system provides representation of the fundamental mode of an airplane wing. The forces calculated are more accurate than the forces which would be predicted for a rigid airframe since the effect of the fundamental mode on the hydrodynamic force is taken into account. In a comparison of the theoretical data with data for a severe flight-test landing impact, the effect of the fundamental mode on the hydrodynamic force is considered and response data are compared with experimental data.
- Investigation of shock diffusers at Mach number 1.85 1: projecting single-shock cones
- Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine design conditions for optimum performance of shock diffusers at Mach number 1.85 with a series of projecting single-shock cones with varying angles. Each cone was tested with a curved and a straight diffuser-inlet section. The effect of angle of attack was investigated for several configurations.
- Investigation of shock diffusers at Mach number 1.85 2: projecting double-shock cones
- Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees.
- Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel
- "An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impossible to obtain satisfactory lateral-flight characteristics even with the increase in height of the vertical tail because of the negative effective dihedral, low directional stability, and large-adverse yawing moments of the ailerons" (p. 1).
- Lateral stability and control characteristics of an airplane model having 42.8 degree sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces
- Report presenting testing in the 300 mph 7- by 10-foot tunnel of an airplane model with a 42.8 degree sweptback wing with an aspect ratio 4.00, taper ratio 0.50, a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine the low-speed lateral stability and control characteristics. Some changes made to improve the aerodynamic characteristics included lowering the wing, incorporating a smaller-fineness-ratio fuselage, and increasing the vertical tail size. Results regarding various configurations, including the semihigh wing with large fuselage, low wing with large fuselage, low wing with small fuselage and small vertical tail, and low wing with small fuselage and large vertical tail are provided.
- Longitudinal Stability and Control Characteristics of an Airplane Model Having a 42.8 Degree Sweptback Circular-Arc Wing With Aspect Ratio 4.00, Taper Ratio 0.50, and Sweptback Tail Surfaces
- Report presenting testing of an airplane model with a 42.8 degree sweptback wing with an aspect ratio of 4.00, taper ratio of 0.50, and a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine its low-speed longitudinal stability and control characteristics. Other variables investigated include the vertical-wing location, fuselage size, horizontal-tail location, and stall-control vanes on the wing.
- The Low-Temperature Solubility of 24 Aromatic Amines in Aviation Gasoline
- Report discussing an investigation of 24 aromatic amines as antiknock additives in aircraft gasolines and their low-temperature solubility.
- Materials Testing Reactor Project : Addendum to Reactor Building Report, Design Report No. 26A
- "Changes, corrections and additions to the original report are included in this addendum. These are brought about by further development of the design by Blaw-Knox, ANL and ORNL. The changes are listed in accordance with the main headings, pages and paragraphs to which they apply."
- The Mathematical Development of the End-Point Method
- Detailed study of the mathematically developed end-point method and its application to the Milne kernel.
- A Method for Predicting the Stability in Roll of Automatically Controlled Aircraft Based on the Experimental Determination of the Characteristics of an Automatic Pilot
- Report presenting a method for predicting the stability of automatically controlled aircraft by comparing the calculated frequency-response curves for the aircraft and experimentally determined frequency-response curves for the automatic pilot. The method is applicable only to stabilization in roll. It can be used to establish the specifications of performance required for the automatic control device for pilotless aircraft designed as missiles.
- NACA Investigation of a Jet-Propulsion System Applicable to Flight
- "Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made" (p. 1).
- Operation of the 184" Cyclotron
- The operation of the 184" synchro-cyclotron is reviewed in terms of the theory as developed by the authors. Certain relevant data on the properties of the magnet and rotating condenser are also presented.
- Performance of 24-Inch Supersonic Axial-Flow Compressor in Air 1: Performance of Compressor Rotor at Design Tip Speed of 1600 Feet Per Second
- Memorandum presenting an investigation of an axial-flow compressor rotor operating with supersonic velocities relative to the blade rows in order to determine the performance characteristics in air and to confirm the performance obtained in Freon-12 at another laboratory. Results regarding the weight flow, work of compression, pressure ratio and adiabatic efficiency, and entry of shock are provided.
- Performance of Compressor of Xj-41-v Turbojet Engine, 3, Compressor Static-Pressure Rise at Equivalent Compressor Speeds of 5000, 7000, 8000, and 9000 RPM
- "At the request of the Air Materiel Command, Army Air Forces, an investigation is being conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The static-pressure variation in the direction of flow through the compressor was presented in reference 1 for an equivalent speed of 8000 rpm. An analysis of these pressure indicated that the maximum-flow limitation of the compressor was caused by separation, which reduced the effective flow area at the vaned-collector entrance" (p. 1).
- Performance of Compressor XJ-41-V Turbojet Engine 1 - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM
- From Summary: "At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compressor, the characteristic performance of each of the compressor components, the state of the air stream in the simulated burner annulus, and the operation of the compressor bearings."
- Polarographic Analysis of UNH in the IAW Stream
- The following report describes two rapid, micro methods for the determination of UNH in Redox waste samples that had been developed fir the concentration range 0.2 to 100 g/l.
- Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine
- Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
- Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92
- Report presenting the damping-in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings in the 9-inch supersonic wind tunnel. The damping in roll of the rectangular wings was very close to what was predicted by linear theory, but the triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind the Mach cone.
- Process Monitor, Mark 10, Model 20
- This report describes a specific apparatus used to monitor the intensity of gamma radiation. The report includes a diagram of the apparatus.
- Qualitative Measurements of Relative Flap Effectiveness at Transonic Speeds on a Series of Five Thin Airfoils With 25-Percent-Chord Flaps and Various Amounts of Sweepback
- Report presenting testing on a series of five flat plate models of aspect ratio 2.0 with 25-percent-mean-aerodynamic-chord flaps at a range of Mach numbers in order to investigate the effect of sweepback on flap effectiveness.
- Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds
- From Summary: "Results are presented of an experimental investigation of the characteristics of NACA submerged inlets on a model of a fighter airplane for Mach numbers from 0.30 to 0.875. The effects on the ram-recovery ratio at the inlets of Mach number, angle of attack, boundary-layer thickness on the fuselage, inlet location, and boundary-layer deflectors are shown. The data indicate only a slight decrease in ram-recovery ratio for the inlets ahead of or just behind the wing leading edge as Mach number increased, but showed large decreases at high Mach numbers for the inlets aft of the point of maximum thickness of the wing."
- Range of U235 Fission Fragments in Photographic Emulsion
- From abstract: "A fine-grain emulsion has been found which is sensitive only to the densely ionizing fission fragments. This emulsion was soaked in uranyl acetate and exposed to slow neutrons. The ranges in the emulsion of about four-hundred fission fragments were measured. The resulting distribution shows a sharp maximum at 23 microns of emulsion. No ternary fissions or large-angle scattering of fragments were observed."
- Recovery of Uranium From Contaminated Precipitron Oil
- Abstract: The distillation and residue extraction recovery procedures developed for the recovery of uranium from Kinney and diffusion pump oil, were applied to contaminated precipitron oil. The effectiveness and advisability of using the method, in whole or in part, is discussed, and various recommendations for processing this particular type of oil are presented. Additional contaminating substances present in this type of oil added to the complexity of the problem but a satisfactory recovery procedure was, nevertheless, successfully developed.
- Resonance Absorption in Lumps and Mixtures
- The resonance absorption of a lump is described in terms of three components. Calculations of resonance absorption are carried out using the model for the resonance spectrum of uranium recently derived; calculations are also made with variations of this model which involve local fluctuations in level strengths. For metal and oxide lumps the agreement with observation is satisfactory. For dilute mixtures, whose resonance activation was measured by Mitchell, computed values fall 20% to 30% above measured ones.
- Separation of Iron and Tuballoy With Phthallic Acid
- Introduction: This report embodies the results of an investigation as to the possibility of removing the bulk of the iron from gunk solutions of various concentrations by precipitation of the iron with phthallic acid and subsequent precipitation of tuballoy. The method consists of dissolving the phthallic acid in the gunk solution and then adding NH₃ to a suitable pH, precipitating the iron, and leaving the tuballoy in solution.
- A simplified theoretical method of determining the characteristics of a lifting rotor in forward flight
- Theoretical derived expressions for the flapping, the thrust, the torque, and the profile drag-lift ratio of nonfeathering rotor with hinged, rectangular, linearly twisted blades are given as simple functions of the inflow velocity and the blade pitch. Representative values of the coefficients of each of the terms in these expressions are tabulated for a series of specified values of the tip-speed ratio. Analysis indicates that the tabulated values can be used to calculate, with reasonable accuracy, the characteristics of any rotor of conventional design.
- Spectra and diffusion in a round turbulent jet
- "In a round turbulent jet at room temperature, measurement of the shear correlation coefficient as a function of frequency (through band-pass filters) has given a rather direct verification of Kolmogoroff's local-isotropy hypothesis. One-dimensional power spectra of velocity and temperature fluctuations, measured in unheated and heated jets, respectively, have been contrasted. Under the same conditions, the two corresponding transverse correlation functions have been measured and compared" (p. 1).
- A Spectrophotometric Determination of Mixtures of Hexavalent and Tetravalent Tuballoy : Preliminary Report
- Report outlining a study that tested the use of colorimetric methods with high concentration phosphoric acid as a solvent for rapid analysis of mixtures of T^+4 and T^+6.
- Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XP-85 Airplane While Attached to the Trapeze
- "At the request of the Air Materiel Command, Army Air Forces, an investigation of the low-speed, power-off, stability and control characteristics of the McDonnell XP-85 airplane has been conducted in the Langley free-flight tunnel. The results of the portion of the investigation consisting of tests of a 1/10-scale model to study the stability of the XP-85 when attached to the trapeze and during retraction into the B-36 bomb bay are presented herein. In the power-off condition the stability was satisfactory with all oscillations well damped and the nose-restraining collar could be placed in position without difficulty" (p. 1).
- Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed
- Symbols and definition of various airspeed terms that have been adopted as standard by the NACA subcommittee on aircraft structural design are presented. The equations, charts, and tables required in the evaluation of true airspeed, calibrated airspeed, equivalent airspeed, impact and dynamic pressures, and Mach and Reynolds numbers have been compiled. Tables of the standard atmosphere to an altitude of 65,000 feet and a tentative extension to an altitude of 100,000 feet are given along with the basic equations and constants on which both the standard atmosphere and the tentative extension are based.
- Summary of the Research Progress Meeting June 17, 1948
- This summary of the research progress meeting on June 17, 1948 discusses the following topics: (1) Potassium 43 (R. Overstreet); (2) Recoils (A. Ghiorso); (3) M.I.T. accelerator conference (W. Panofsky); and (4) Cosmic rays (Prof. Louis Le prince - Ringuet, France)
- Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336
- Tests of a powered dynamic model of the Columbia XJL-1 amphibian were made in Langley tank no.1 to determine the hydrodynamic stability and spray characteristics of the basic hull and to investigate the effects of modifications on these characteristics. Modifications to the forebody chime flare, the step, and the afterbody, and an increase in the angle of incidence of the wing were included in the test program. The seaworthiness and spray characteristics were studied from simulated taxi runs in smooth and rough water. The trim limits of stability, the range of stable positions of the enter of gravity for take-off, and the landing stability were determined in smooth water. The aerodynamic lift, pitching moment, and thrust were determined at speeds up to take-off speed.