National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-Oxygen Mixtures Assuming Equilibrium Composition

Description: "Theoretical rocket performance for equilibrium composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity… more
Date: February 25, 1958
Creator: Gordon, Sanford
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of a high-temperature static strain gage to the measurement of thermal stresses in a turbine stator vane

Description: From Introduction: "This report describes the high-temperature static strain gage and presents the results obtained in a determination of the thermal stresses in a turbine stator vane resulting from the temperature distribution obtained under steady-state conditions at rated speed and temperature of the engine."
Date: March 1958
Creator: Kemp, R. H.; Morse, C. R. & Hirschberg, M. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximations for the thermodynamic and transport properties of high-temperature air

Description: Report presenting the thermodynamic and transport properties of high-temperature air in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, specific heats, speed of sound, coefficients of viscosity and thermal conductivity, and Prandtl numbers for air are provided for a range of temperatures and pressures.
Date: March 1958
Creator: Hansen, C. Frederick
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drop-size distributions for impinging-jet breakup in airstreams simulating the velocity conditions in rocket combustors

Description: Report presenting drop-size-distribution data obtained for heptane sprays produced by pairs of impinging jets in airstreams over ranges of orifice diameter, liquid-jet velocity, and velocity difference between the airstream and the liquid jet.
Date: March 1958
Creator: Ingebo, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of a stringer on the stress concentration due to a crack in a thin sheet

Description: From Summary: "A coefficient is obtained for determining the effect of reinforcing stringer on the stress concentration factor at the tip of a crack in a thin sheet. The results are given for the case in which the stringer is intact and for the case in which the stringer is broken. In the first case the stress concentration factor for the stringer is also given."
Date: March 1958
Creator: Sanders, J. Lyell, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of jet temperature on jet-noise generation

Description: Report presenting an experimental investigation in order to determine the effect of jet temperature on jet-noise generation. Jet pressure ratios from 1.3 to 1.9 and temperature from 80 to 1000 degrees Fahrenheit. Results showed that sound power can be adequately predicted by the Lighthill parameter based on ambient temperature over the range of temperatures investigated.
Date: March 1958
Creator: Rollin, Vern G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of overheating on creep-rupture properties of M-252 alloy

Description: Report presenting a study on the influence of periodic overheats of 2-minutes duration to four different temperatures on the creep-rupture properties of M-252 alloy at 1500 degrees Fahrenheit. The purpose of the study was to provide information regarding the estimation of the effects of overheating on creep-rupture performance of gas-turbine parts. Results regarding normal rupture properties of experimental materials, overheats on heat HT-28, overheats on heats 837 and 43642, comparative effect… more
Date: March 1958
Creator: Rowe, John P. & Freeman, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Wall Cooling on Inlet Parameters of a Scoop Operating in a Turbulent Boundary Layer on a Flat or Conical Surface for Mach Numbers 2 to 10

Description: Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.
Date: March 1958
Creator: Beke, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube

Description: "Ideally, the reflection of a shock from the closed end of a shock tube provides, for laboratory study, a quantity of stationary gas at extremely high temperature. Because of the action of viscosity, however, the flow in the real case is not one-dimensional, and a boundary layer grows in the fluid following the initial shock wave. In this paper simplifying assumptions are made to allow an analysis of the interaction of the shock reflected from the closed end with the boundary layer of the initi… more
Date: March 1958
Creator: Mark, Herman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Aperiodic Time Processes With Autocorrelation and Fourier Analysis

Description: "Autocorrelation and frequency analyses of a series of aperiodic time events, in particular, filtered noises and sibilant sounds, were made. The position and band width of the frequency ranges are best obtained from the frequency analysis, but the energies contained in the several bands are most easily obtained from the autocorrelation function. The mean number of zero crossings of the time function was determined from the curvature of the latter function in the vicinity of the zero crossing, a… more
Date: March 1958
Creator: Exner, Marie Luise
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of total hemispherical emissivity of various oxidized metals at high temperature

Description: Report presenting the results of measurements of total hemispherical emissivity at high temperatures for various metals are presented together with a limited description of the equipment and procedures used. Results regarding stainless steel, mild steel, titanium alloy, titanium, copper, aluminum, molybdenum, and tantalum are provided.
Date: March 1958
Creator: Wade, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method for the Calculation of Wave Drag on Supersonic-Edged Wings and Biplanes

Description: "A method is presented for finding the lift, moment, and drag on three-dimensional wings or biplanes with supersonic edges and a straight trailing edge normal to the free stream. The minimum wave drag for fixed lift or volume is given for several special cases. Simple applications of the method may provide some measure of the degree to which more abstract method for finding minima can be relied upon as a measure of optimum real systems" (p. 1).
Date: March 1958
Creator: Lomax, Harvard & Sluder, Loma
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Prandtl-Meyer expansion of chemically reacting gases in local chemical and thermodynamic equilibrium

Description: "It is found that Prandtl-Meyer flow, in which chemical reactions are occurring and are in equilibrium, can be simply and exactly calculated. The property of air which governs the flow is found to be a quantity which depends only on the ratio of enthalpy to the square of the speed of sound; the analogous quality for an inert gas depends only on the ratio of specific heats. the maximum angle through which the flow may turn is generally larger when chemical reactions are occurring than it is in n… more
Date: March 1958
Creator: Heims, Steve P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure distributions at transonic speeds for parabolic-arc bodies of revolution having fineness ratios of 10, 12, and 14

Description: From Summary: "The measured static-pressure distributions at the model surfaces and in the surrounding flow field are presented for parabolic-arc bodies of revolution having fineness ratios of 10, 12, and 14. The data were obtained with the various bodies at zero angle of attack. The Mach number varied from 0.80 to 1.20, and Reynolds number varied from approximately 23.4 x 10(exp 6) to 28.6 x 10(exp 6) (based on the theoretical length of the model from nose to point of closure)."
Date: March 1958
Creator: Taylor, Robert A. & McDevitt, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Propellant vaporization as a criterion for rocket engine design; Relation between percentage of propellant vaporized and engine performance

Description: Report presenting an anakysis of the quantitative effect of incomplete propellant vaporization on rocket-engine performance. Results regarding the effect of incomplete vaporization on engine performance and an interpretation of experimental data are provided.
Date: March 1958
Creator: Heidmann, Marcus F. & Priem, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Skin-friction measurements in incompressible flow

Description: Report presenting experiments conducted to measure in incompressible flow the local surface-shear stress and average skin-friction coefficient for a turbulent boundary layer on a smooth, flat plate with zero pressure gradient. Local velocity measurements and local surface-shear measurements were taken and a sensitive manometer was used.
Date: March 1958
Creator: Smith, Donald W. & Walker, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transient Heating Effects on the Bending Strength of Integral Aluminum-Alloy Box Beams

Description: Note describing tests of twenty-five square-tube beams made of aluminum alloy under various combinations of bending moment and transient heating. Two types of heat input were used so that the effect of thermal stresses could be separated from effects of material properties. Two sizes of square tubes were tested so that both elastic and plastic buckling stresses would be obtained.
Date: March 1958
Creator: Pride, Richard A. & Hall, John B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wall Pressure Fluctuations in a Turbulent Boundary Layer

Description: Note presenting an investigation of sound generation that is generated by turbulence on a solid surface. Suitable equipment has been developed to measure the fluctuating wall pressure in the turbulent boundary layer. Results regarding the response of the transducer in a laminar and turbulent boundary layer, power-spectrum measurements, and mean-square pressure measurements are provided.
Date: March 1958
Creator: Willmarth, William W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight study of longitudinal-control-system dynamic characteristics by the use of a variable-control-system airplane

Description: Report presenting flight tests with an airplane equipped to vary the longitudinal-control-system dynamic characteristics over a wide range. Control is obtained through a stabilizer force-command position-feedback longitudinal-control system. Results at a Mach number of 0.80 at 35,000 feet altitude, Mach number of 0.35 at 5,000 feet altitude, and normal-acceleration response are provided.
Date: March 3, 1958
Creator: McFadden, Norman M.; Pauli, Frank A. & Heinle, Donovan R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static Longitudinal and Lateral Stability and Control Characteristics of a Model of a Swept-Wing Fighter-Bomber-Type Airplane With a Top Inlet at Mach Numbers From 1.6 to 2.35

Description: "Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).
Date: March 3, 1958
Creator: Gnos, A. Vernon & Kurkowski, Richard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957

Description: "A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records" (p. 1).
Date: March 3, 1958
Creator: Copp, Martin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds

Description: Report presenting an investigation of the jet effects on several afterbody shapes of a single-engine fighter-airplane model in the 16-foot transonic tunnel at a range of Mach numbers and angles of attack. The afterbody-geometry variables were boattail angle, afterbody length, and base area. Results regarding evaluation of support interference, afterbody-pressure-distribution characteristics, and drag characteristics are provided.
Date: March 4, 1958
Creator: Norton, Harry T., Jr. & Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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