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  • Other Sources  (842)
  • ENERGY PRODUCTION AND CONVERSION  (452)
  • AERODYNAMICS  (383)
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  • 1975-1979  (840)
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  • 1975-1979  (840)
  • 1970-1974
  • 1920-1924
  • 1915-1919  (2)
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  • 101
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    Unsteady flow in a supersonic cascade with strong in-passage shocks (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Linearized theory is used to study the unsteady flow in a supersonic cascade with in-passage shock waves. We use the Wiener-Hopf technique to obtain a closed-form analytical solution for the supersonic region. To obtain a solution for the rotational flow in the subsonic region we must solve an infinite set of linear algebraic equations. The analysis shows that it is possible to correlate quantitatively the oscillatory shock motion with the Kutta condition at the trailing edges of the blades. This feature allows us to account for the effect of shock motion on the stability of the cascade. Unlike the theory for a completely supersonic flow, the present study predicts the occurrence of supersonic bending flutter. It therefore provides a possible explanation for the bending flutter that has recently been detected in aircraft-engine compressors at higher blade loadings.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 83; Dec. 5
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  • 102
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    Correlation of turbulent shear layer attachment peak heating near Mach 6 (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A correlation of new turbulent two-dimensional data and peak heating data for attaching free shear layers is presented for a 2.54-cm and 5.08-cm diam cylindrical leading-edge slab 25.4 cm long, and 7.62 and 10.16 cm wide. A 30.48 x 25.4 cm sharp leading-edge flat plate set at 15 and 20 deg is used to generate plane impinging shocks. The freestream Mach number is 6 and the freestream Reynolds number varies from 3,300,000 to 25,600,000/m. Peak heating is measured on silica-based epoxy models with a phase change coating technique. A comparison of the free shear layer data with the transition data of Birch and Keyes (1972) reveals that the shear layer data are turbulent at attachment. The trend of the data shows that peak heating is strongly affected by the state of development at attachment. As the free shear layers become more fully developed, the data approach the two-dimensional correlation. Persistence of transitional flow structures for supersonic free shear flows is pointed out.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Dec. 197
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  • 103
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    Calculated heating on the afterbody nozzle of a hypersonic aircraft concept (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The present analysis was carried out to estimate the heating levels of the external nozzle of a scramjet/airframe-integrated research aircraft. A parametric examination of the effects of Mach number, reference length, and wall temperature showed that the heating rate distributions are independent of reference length and wall temperature. The initial heating rates obtained for a Mach 6 flight are in the (3 to 8) x 10 to the 5th power W/sq m range. Underlying the entire study is the question of nozzle boundary layer formation and growth, as well as the question of the reference length value that should be used in the computations. It is shown that the reference length is not the dominant factor setting the heating levels; an attempt to bound the actual length was made. A more detailed calculation of the rates requires further work to gain a better understanding of the combustor exit boundary layer.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; Dec. 197
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  • 104
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    Solar air heaters and their applications (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The solar air heater appears to be the most logical choice, as far as the ultimate application of heating air to maintain a comfortable environment is concerned. One disadvantage of solar air heaters is the need for handling larger volumes of air than liquids due to the low density of air as a working substance. Another disadvantage is the low thermal capacity of air. In cases where thermal storage is needed, water is superior to air. Design variations of solar air heaters are discussed along with the calculation of the efficiency of a flat plate solar air heater, the performance of various collector types, and the applications of solar air heaters. Attention is given to collectors with nonporous absorber plates, collectors with porous absorbers, the performance of flat plate collectors with finned absorbers, a wire mesh absorber, and an overlapped glass plate air heater.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 105
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    Energy resources of the developing countries and some priority markets for the use of solar energy (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Energy consumption for the developed and non-developed world is expressed as a function of GNP. An almost straight-line graph results when energy consumption statistics are treated in this manner. The richest countries consume the most energy, and the poorest countries the least. It therefore follows that greater energy production in the developing countries (leading to greater energy consumption) will contribute to their economic growth. Energy resources in the developing countries are compared, including: solid fossil fuels, crude oil, natural gas, oil shale, and uranium. Mention is also made of the potential of renewable energy resources, such as solar, wind, and hydroelectric power, in the underdeveloped world; and it is these resources which offer the greatest possibilities for economic improvement if the money is forthcoming, i.e., from the world bank, to fund the necessary technology.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Journal of Energy and Development; 3; Autumn 1
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  • 106
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    Aerodynamic characteristics at high angles of attack (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An overview is presented of the aerodynamic inputs required for analysis of flight dynamics in the high-angle-of-attack regime wherein large-disturbance, nonlinear effects predominate. An outline of the presentation is presented. The discussion includes: (1) some important fundamental phenomena which determine to a large extent the aerodynamic characteristics of airplanes at high angles of attack; (2) static and dynamic aerodynamic characteristics near the stall; (3) aerodynamics of the spin; (4) test techniques used in stall/spin studies; (5) applications of aerodynamic data to problems in flight dynamics in the stall/spin area; and (6) the outlook for future research in the area.
    Keywords: AERODYNAMICS
    Type: Von Karman Inst. for Fluid Dyn. Aerodyn. Inputs for Probl. in Aircraft Dyn., Vol. 2; 39 p
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  • 107
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    Vortex attenuation flight experiments (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flight tests evaluating the effects of altered span loading, turbulence ingestion, combinations of mass and turbulence ingestion, and combinations of altered span loading turbulance ingestion on trailed wake vortex attenuation were conducted. Span loadings were altered in flight by varying the deflections of the inboard and outboard flaps on a B-747 aircraft. Turbulence ingestion was achieved in flight by mounting splines on a C-54G aircraft. Mass and turbulence ingestion was achieved in flight by varying the thrust on the B-747 aircraft. Combinations of altered span loading and turbulence ingestion were achieved in flight by installing a spoiler on a CV-990 aircraft and by deflecting the existing spoilers on a B-747 aircraft. The characteristics of the attenuated and unattenuated vortexes were determined by probing them with smaller aircraft. Acceptable separation distances for encounters with the attenuated and unattenuated vortexes are presented.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 369-403
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  • 108
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    Ground-based facilities for evaluating vortex minimization concepts (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: To determine the feasibility of altering the formation and decay of aircraft trailing vortexes through aerodynamic means, the test capabilities of two wind tunnels and two towing basins were used. The facilities, common models, and measurement techniques that were employed in the evaluation of vortex minimization concepts are described.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 129-156
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  • 109
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    Recent developments in photovoltaic energy by ERDA/NASA-LeRC (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Application development activities were designed to stimulate the market for photovoltaics so that as costs are reduced there will be an increasing market demand to encourage the expansion of industrial solar array production capacity. Supporting these application development activities are tasks concerned with: (1) establishing standards and methodology for terrestrial solar cell calibration; (2) conducting standard and diagnostic measurements on solar cells and modules; and (3) conducting real time and accelerated testing of solar cell modules and materials of construction under outdoor sunlight conditions.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Proc. of the ASPE(MSFC Symp. on Eng. and Productivity Gains from Space Technol.; p 69-85
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  • 110
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    Estimation of outgassing from an expended apogee motor and its effects on spacecraft surfaces (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An experimental and theoretical investigation was carried out to evaluate the degradation of the solar cells and other sensitive surfaces of a spacecraft, resulting from the molecular outgassing of an expended solid propellant apogee motor. The motor, following its burnout, is retained by the spacecraft and is a source of gases and particulates which will be released mainly by the unburned propellant-to-casing insulation. The deployment of the solar array within a few minutes after the motor burn results in the interception and reflection to the surfaces of the spacecraft of the molecular outgassing and particulates. Various methods, based on some experimental data, were used to analytically assess the magnitude of the outgassing from the engine.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Goddard Space Flight Center Ninth Conf. on Space Simulation; p 221-241
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  • 111
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    Solar panel acceptance testing using a pulsed solar simulator (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Utilizing specific parameters as area of an individual cell, number in series and parallel, and established coefficient of current and voltage temperature dependence, a solar array irradiated with one solar constant at AMO and at ambient temperature can be characterized by a current-voltage curve for different intensities, temperatures, and even different configurations. Calibration techniques include: uniformity in area, depth and time, absolute and transfer irradiance standards, dynamic and functional check out procedures. Typical data are given for individual cell (2x2 cm) to complete flat solar array (5x5 feet) with 2660 cells and on cylindrical test items with up to 10,000 cells. The time and energy saving of such testing techniques are emphasized.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Goodard Space Flight Center Ninth Conf. on Space Simulation; p 27-45
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  • 112
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    Coal feed component testing for CDIF (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Investigations conducted during the conceptual design of the Montana MHD Component Development and Integration Facility (CDIF) identified commercially available processing and feeding equipment potentially suitable for use in a reference design. Tests on sub-scale units of this equipment indicated that they would perform as intended.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: JPL Proc. of the Conf. on Coal Feeding Systems; p 550-570
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  • 113
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    Ground development and flight correlation of the vortex attenuating spline device (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Data presented indicate that the wing-mounted spline is a effective vortex-attenuating device. A comparison of the vortex induced rolling moment results at a separation scale distance of 0.70 km with those measured in full scale flight indicate good agreement for the unattenuated vortex configuration. The comparison also indicates that the spline effectiveness in flight was greater than in the ground facility test. The results of an applications study show that, for the heavy commercial jet aircraft studied, use of the splines does result in some degradation of the climb gradient and rate of climb, but the aircraft should meet certification requirements.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 271-303
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  • 114
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    Application of laser velocimetry to aircraft wake-vortex measurements (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The theory and use of a laser velocimeter that makes simultaneous measurements of vertical and longitudinal velocities while rapidly scanning a flow field laterally are described, and its direct application to trailing wake-vortex research is discussed. Pertinent measurements of aircraft wake-vortex velocity distributions obtained in a wind tunnel and water towing tank are presented. The utility of the velocimeter to quantitatively assess differences in wake velocity distributions due to wake dissipating devices and span loading changes on the wake-generating model is also demonstrated.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 157-192
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  • 115
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    Wind energy: A renewable energy option (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Wind turbine generator research programs administered by the Energy Research and Development Administration are examined. The design and operation of turbine demonstration models are described. Wind assessments were made to determine the feasibility of using wind generated power for various parts of the country.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Marshall Space Flight Center Proc. of the ASPE(MSFC Symp. on Eng. and Productivity Gains from Space Technol.; p 33-68
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  • 116
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    Ocean Thermal Energy Conversion (OTEC) (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Energy Research and Development Administration research progress in Ocean Thermal Energy Conversion (OTEC) is outlined. The development program is being focused on cost effective heat exchangers; ammonia is generally used as the heat exchange fluid. Projected costs for energy production by OTEC vary between $1000 to $1700 per kW.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Marshall Space Flight Center Proc. of the ASPE(MSFC Symp. on Eng. and Productivity Gains from Space Technol.; p 87-94
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  • 117
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    Impact of alternative energy forms on public utilities (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The investigation of alternative energy sources by the electric utility industry is discussed. Research projects are reviewed in each of the following areas; solar energy, wind energy conversion, photosynthesis of biomass, ocean thermal energy conversion, geothermal energy, fusion, and the environmental impact of alternative energy sources.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Marshall Space Flight Center Proc. of the ASPE(MSFC Symp. on Eng. and Productivity Gains from Space Technol.; p 19-31
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  • 118
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    Effect of compliant wall motion on turbulent boundary layers (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A critical analysis of available wall data which indicated drag reduction under turbulent boundary layers. Detailed structural dynamic calculations suggest the surfaces responded in a resonant, rather than compliant, manner. Alternate explanations are given for drag reductions observed in two classes of experiments: flexible pipe flown, and waterbacked membranes in air. Analysis indicates the wall motion for the remaining data is typified by short wave lengths in agreement with the requirement of a possible compliant wall drag reduction mechanism recently suggested by Langley.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Concepts for Drag Reduction; 26 p
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  • 119
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    Methods for Reducing Subsonic Drag Due to Lift (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The results of repeat experimental research on methods for reducing subsonic drag due to lift are discussed. The NASA supercritical airfoils and their application to structurally practical wings with increased aspect radio are described. A design approach and experimental results for wing-tip-mounted winglets are presented. Several methods for utilizing the thrust of jet engines to provide reductions in the drag due to lift are also discussed.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Concepts for Drag Reduction; 17 p
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  • 120
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    Efficient solution of unsteady transonic flows about airfoils (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: An implicit finite difference procedure was developed for the efficient solution of unsteady transonic flow fields. Sample computations illustrate applications of procedures to aerodynamic problems. Solutions are presented that illustrate three types of shock wave motion that can result from airfoil control surface oscillations. The significant effect of wind tunnel wall conditions on these shock wave motions is demonstrated. Solutions are also presented for a simple aeroelastic problem in which the flow field equations and the structural motion equations are integrated simultaneously in time. Both stable and unstable aeroelastic interactions are considered. The procedure is adapted to compute unsteady aerodynamic force coefficients by the indicial method.
    Keywords: AERODYNAMICS
    Type: AGARD Unsteady Airloads in Separated and Transonic Flow; 11 p
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  • 121
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    Assessment of existing analytic methods for prediction of high angle-of-attack loads on delta wings at supersonic speeds (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: An assessment of the applicability of four loading prediction methods to high angle-of-attack conditions for simplified wing-body configurations is provided. The methods are: The tangent wedge approximation, the linear theory methods of Middleton and Woodward, and a shock-fitting finite-difference technique. Estimates obtained by these methods were compared with experimental pressure data on delta wings to examine the effects of Mach number, camber, sweep angle, and angle of attack. Results indicate that all of the methods provided reasonable estimates at moderate angles of attack. At these moderate angles of attack, the methods of Middleton and Woodward provided good estimates at Mach numbers higher than those usually associated with linear theory. Only the finite-difference method provided reasonable load estimates at high angles of attack.
    Keywords: AERODYNAMICS
    Type: AGARD Prediction of Aerodynamic Loading; 7 p
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  • 122
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    Comparisons of Theoretical and Experimental Pressure Distributions on an Arrow-Wing Configuration at Subsonic, Transonic, and Supersonic Speeds (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A wind tunnel test of an arrow wing body configuration consisting of flat and twisted wings, as well as a variety of leading- and trailing-edge control surface deflection, has been conducted at Mach numbers from 0.40 to 2.50 to provide an experimental data base for comparison with theoretical methods. Theory-to-experiment comparisons of detailed pressure distributions have been made using current state-of-the-art attached- and separated-flow methods. The purpose of these comparisons was to delineate conditions under which these theories are valid for aeroelastic calculations and to explore the use of empirical methods to correct the theoretical methods where theory is deficient. It was determined that current state-of-the-art attached flow and empirical methods were inadequate to predict aeroelastic loads for this configuration.
    Keywords: AERODYNAMICS
    Type: AGARD Prediction of Aerodynamic Loading; 14 p
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  • 123
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    Inviscid modeling of aircraft trailing vortices (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A survey is presented of inviscid theoretical methods that are useful in the study of lift-generated vortices. Concepts derived using these invisicid theories are cited which have helped to guide research directed at alleviating the velocities and rolling moments imposed on aircraft entering these wakes.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 9-60
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  • 124
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    Space solar power systems (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Studies were done on the feasibility of placing a solar power station called POwersat, in space. A general description of the engineering features are given as well as a brief discussion of the economic considerations.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lyndon B. Johnson Space Center Bioprocessing in Space; p 191-204
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  • 125
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    Unsteady aerodynamic modeling for arbitrary motions (1977)
    In:  Other Sources
    Details
    Publication Date: 2015-11-05
    Description: Results indicating that unsteady aerodynamic loads derived under the assumption of simple harmonic motions executed by airfoil or wing can be extended to arbitrary motions are summarized. The generalized Theodorsen (1953) function referable to loads due to simple harmonic oscillations of a wing section in incompressible flow, the Laplace inversion integral for unsteady aerodynamic loads, calculations of root loci of aeroelastic loads, and analysis of generalized compressible transient airloads are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; Volume 15; Apr. 1977
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  • 126
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    The development and use of spoilers as vortex attenuators (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results are presented of groundbased and flight investigations performed to develop spoilers as trailing vortex alleviation devices. Based on the results obtained in these investigations, it was found that the induced rolling moment on a trailing model can be reduced by spoilers located near the midsemispan of a vortex generating wing. Substantial reductions in induced rolling moment occur when the spoiler vortex attenuator is located well forward on both unswept and swept wing models. In addition, it was found that existing flight spoilers on the jumbo-jet transport aircraft can be effective as trailing vortex attenuators.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 339-368
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  • 127
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    Unsuccessful Concepts for Aircraft Wake Vortex Minimization (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Exploratory concepts are described which were investigated to achieve a reduction in the vortex induced rolling upsets produced by heavy aircraft trailing vortexes. The initial tests included the use of mass injection, oscillating devices, wingtip shape design, interacting multiple vortexes, and end plates. Although later refinements of some of these concepts were successful, initial test results did not indicate a capability of these concepts to significantly alter the vortex induced rolling upset on a following aircraft.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 221-250
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  • 128
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    Flight test techniques for wake-vortex minimization studies (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flight test techniques developed for use in a study of wake turbulence and used recently in flight studies of wake minimization methods are discussed. Flow visualization was developed as a technique for qualitatively assessing minimization methods and is required in flight test procedures for making quantitative measurements. The quantitative techniques are the measurement of the upset dynamics of an aircraft encountering the wake and the measurement of the wake velocity profiles. Descriptions of the instrumentation and the data reduction and correlation methods are given.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 193-220
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  • 129
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    Aircraft wake-vortex minimization by use of flaps (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A survey was made of research on the alleviation of the trailing vortex hazard by altering span loading with flaps on the generator airplane. Flap configurations of the generator that shed multiple vortices were found to have wakes that dispersed by vortex merging and sinusoidal instability. Reductions of approximately 50 percent in both the wake rolling moment imposed on a following aircraft and the aircraft separation requirement were achieved in the ground based and flight test experiments by deflecting the trailing edge flaps more inboard than outboard. Significantly, this configuration did not increase the drag or vibration on the generating aircraft compared to the conventional landing configuration. Ground based results of rolling moment measurement and flow visualization are shown, using a water tow facility, an air tow facility, and a wind tunnel. Flight test results are also shown, using a full scale B-747 airplane. General agreement was found among the results of the various ground based facilities and the flight tests.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 305-338
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  • 130
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    Thrust-augmented vortex attenuation (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An experimental investigation was conducted to determine the vortex attenuating effect of engine thrust. Tests were made using a 0.03-scale model of the Boeing 747 transport aircraft as a vortex generating model. A Learjet-class probe model was used to measure the vortex induced rolling moment at a scale separation distance of 1.63 km. These tests were conducted at a lift coefficient of 1.4 at a model velocity of 30.48 m/s. The data presented indicate that engine thrust is effective as a vortex attenuating device when the engines are operated at high thrust levels and are positioned to direct the high energy engine wake into the core of the vortex. The greatest thrust vortex attenuation was obtained by operating the inboard engine thrust reversers at one-quarter thrust and the outboard engines at maximum forward thrust.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 251-270
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  • 131
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    Investigation of a CTS solar cell test patch under simulated geomagnetic substorm charging conditions (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The CTS solar array technology experiment which consists of a solar cell test patch on the Kapton-substrate solar array and the appertaining electronics unit has been operating in geostationary orbit for nearly 1 year without any malfunction although it is expected to be strongly influenced by charging effects on the array surface. The results of a post-launch test program show that the experiment would not survive a discharge due to electrostatic charging in the test patch area. In a simulated substorm, environment discharges were obtained only below a temperature threshold of about 30 C. With solar illumination, this threshold is reduced below 0 C.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Res. Center Proc. of the Spacecraft Charging Technol. Conf.; p 487-501
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    ERDA's central receiver solar thermal power system studies (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The utilization of solar energy for electrical power production was studied. Efforts underway on the central receiver solar thermal power system are presented. Preliminary designs are included of pilot plant utilizing large numbers of heliostats in a collector field. Safety hazards are also discussed, as well as the most beneficial location of such a plant within the United States.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Marshall Space Flight Center Proc. of the ASPE(MSFC Symp. on Eng. and Productivity Gains from Space Technol.; p 95-123
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  • 133
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    ERDA/NASA-MSFC solar heating and cooling development and demonstration program (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The role of the Manned Space Flight Center (MSFC) in the National Solar Heating and Cooling program is evaluated. The responsibilities of the MSFC within this program are (1) to manage the development and testing of solar heating and cooling systems leading to marketable products, (2) to develop data acquisition equipment supporting a national data program, and (3) to manage and collect data from commercial demonstration sites. MSFC test facilities and demonstration sites are described.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Proc. of the ASPE(MSFC Symp. on Eng. and Productivity Gains from Space Technol.; p 9-17
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  • 134
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    Slot injection for skin-friction drag reduction (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A description and analysis of slot injection in low-speed flow, slot injection in high-speed flow, a discussion of aircraft applications, and possibilities for future improvements of slot drag reduction capability are presented.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Concepts for Drag Reduction; 11 p
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  • 135
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    An overview of concepts for aircraft drag reductions (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A current overview of aerodynamic drag reduction concepts which have potential for reducing aircraft fuel consumption is presented. The discussion shows where the greatest percentages of aircraft fuel is burned and what areas have the greatest potential for fuel conservation. The paper deals with aerodynamic improvements and touches only briefly on structural and propulsion improvements. Concepts for reducing pressure drag (i.e., roughness, wave, interference, and separation drag), drag due to lift/induced drag, and skin-friction drag at subsonic and supersonic speeds are emphasized.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Concepts for Drag Reduction; 30 p
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  • 136
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    Laminar flow control laminarization (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A practical aerodynamically and structurally reasonably efficient laminar flow control (LFC) suction method, removing the slowest boundary layer particles through many closed spaced fine slots, was developed and subsequently applied to a second F94 LFC wing glove in flight: 100 percent laminar flow was observed up to the F94 test limit. Laminar flow on LFC wings in flight is thus possible at a much higher Reynold's number than even in the best low turbulence tunnels as a result of the negligible influence of the atmospheric microscale turbulence on transition. The F94 LFC glove comparison experiments, with suction starting at 0.03c and 0.4c, verified the theoretically predicted boundary layer stabilization by suction starting at 0.08c, thus maintaining laminar flow at substantially higher C sub L numbers as compared to boundary layer stabilization by flow acceleration; i.e., geometry alone without suction upstream of 0.4c.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Concepts for Drag Reduction; 75 p
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  • 137
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    Aerodynamic loads near cranks, apexes, and tips of thin, lifting wings in incompressible flow (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The calculation of the incompressible and irrotational flow in the vicinity of tips and corners of thin, lifting wings is considered. It is shown that the important characteristics of the flow are governed by an eigenvalue problem, which is nonlinear at the trailing edge because of the shed wake (assumed to be in the wing plane). A new solution method was devised because either the existing methods were not valid for the trailing edge case or they would have required excessive amounts of computer time. The new method, which is fundamentally different than the previous ones, was used to calculate solutions for a number of cases, including some for which correct answers had not previously been obtained. Two of these solutions were used to determine the validity of drag and leading-edge-suction distributions near the tips of a delta wing and a swept wing as calculated by using both the vortex lattice method and a kernel function method. The calculations for the swept wing resolved the question of whether or not the induced drag should be zero at the wing tip.
    Keywords: AERODYNAMICS
    Type: AGARD Prediction of Aerodynamic Loading; 12 p
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  • 138
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    Experimental studies of flow separation of the GA(W)-2 airfoil at low speeds (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests have been conducted on a NASA GA(W)-2 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 10.3, 14.4, and 18.3 deg. Pre- and post-separated velocity and pressure survey results over the airfoil and in the associated wake are presented. Extensive force, pressure, tuft survey, hot-film survey, local skin friction, and boundary layer data are also included. Pressure distributions and separation point locations show good agreement with theory for the two lower angles of attack. Boundary layer displacement thickness, momentum thickness, and shape factor agree well with theory up to the point of separation. There is considerable disparity between extent of flow reversal in the wake as measured by pressure and hot-film probes. The difference is attributed to the intermittent nature of the flow reversal.
    Keywords: AERODYNAMICS
    Type: NASA-CR-197254 , NAS 1.26:197254 , AR77-4
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  • 139
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    Computer program to prepare airfoil characteristic data for use in helicopter performance calculations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program developed to prepare wind tunnel generated airfoil data for input into helicopter performance prediction programs is described. The program provides for numerically cross plotting the data, plotting the data, and tabulating and punching the tabulated result into computer cards for use in the rotorcraft flight simulation model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78627 , L-11608
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  • 140
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    Solar energy heating system design package for a single-family residence at New Castle, Pennsylvania (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design of a solar heating and hot water system for a single family dwelling is described. Cost trade studies on the energy conservation and architectural features of the solar house are discussed. The present status of verification for the single family heating system, i.e., proof that the components and the system meet applicable physical and functional requirements, is reported. The system integration drawings, the major subsystems drawings, and the architect's specifications and plans are included.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-161356
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  • 141
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    Solar heating system design package for a single-family residence at William O'Brien State Park, Minnesota (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The plans, specifications, cost trade studies, and verification status of a prototype solar heating and hot water system for the Minnesota Department of Natural Resources's single-family dwelling located at O'Brien State Park, 30 miles east of Minneapolis, Minnesota are presented.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-161357
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  • 142
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    Qualification test procedures and results for Honeywell solar collector subsystem, single-family residence (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test procedures and results in qualifying the Honeywell single family residence solar collector subsystem are presented. Testing was done in the following areas: pressure, service loads, hail, solar degradation, pollutants, thermal degradation, and outgassing.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-161382
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  • 143
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    Solar heating system installed at Telex Communications, Inc., Blue Earth, Minnesota (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The solar heating system for space heating a 97,000 square foot building which houses administrative offices, assembly areas, and warehouse space is summarized. Information on system description, test data, major problems and resolutions, performance, operation and maintenance manual, manufacturer's literature, and as-built drawings is presented.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-161437
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  • 144
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    Two-dimensional wind-tunnel tests of a NASA supercritical airfoil with various high-lift systems. Volume 1: Data analysis (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: High-lift systems for a NASA, 9.3%, method for calculating the viscous flow about two-dimensional multicomponent airfoils was evaluated by comparing its predictions with test data. High-lift systems derived from supercritical airfoils were compared in terms of performance to high-lift systems derived from conventional airfoils. The high-lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: a single-slotted flap; a double-slotted flap and a leading-edge slat; and a triple-slotted flap and a leading-edge slat. Agreement between theoretical predictions and experimental results are also discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2214 , D6-41063-1-VOL-1
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  • 145
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    Two-dimensional wind-tunnel tests of a NASA supercritical airfoil with various high-lift systems. Volume 2: Test data (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three high lift systems for a 9.3 percent blunt based, supercritical airfoil were designed, fabricated, and wind tunnel tested. A method for calculating the viscous flow about two dimensional multicomponent airfoils was evaluated by comparing its predictions with test data. A comparison of high lift systems derived from supercritical airfoils with high lift systems derived from conventional airfoils is presented. The high lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: (1) a single slotted flap, (2) a double slotted flap and a leading edge slat, and (3) a triple slotted flap and a leading edge slat. Aerodynamic force and moment data and surface pressure data are presented for all configurations and boundary layer and wake profiles for the single slotted flap configuration. The wind-tunnel models, test facilities and instrumentation, and data reduction are described.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2215 , D6-41063-2-VOL-2
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  • 146
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    Comparison of experimental and theoretical drag characteristics for a 10-percent-thick supercritical airfoil using a new version of an analysis code (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Comparisons of experimental and theoretical drag characteristics for a 10-percent-thick supercritical airfoil using a new version of an advanced analysis code. Comparisons are made at near-design normal-force coefficients for Reynolds numbers from 2 to 11 million. Comments are made concerning various input parameters to the code.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-74041 , NAS 1.15:X-74041
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  • 147
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    Finite-element solutions for geothermal systems (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Vector potential and scalar potential are used to formulate the governing equations for a single-component and single-phase geothermal system. By assuming an initial temperature field, the fluid velocity can be determined which, in turn, is used to calculate the convective heat transfer. The energy equation is then solved by considering convected heat as a distributed source. Using the resulting temperature to compute new source terms, the final results are obtained by iterations of the procedure. Finite-element methods are proposed for modeling of realistic geothermal systems; the advantages of such methods are discussed. The developed methodology is then applied to a sample problem. Favorable agreement is obtained by comparisons with a previous study.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Journal of Energy; 1; Nov
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  • 148
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    Simulation of space radiation effects on polyimide film materials for high temperature applications (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Space environment effects on candidate materials for the solar sail film are determined. Polymers, including metallized polyimides that might be suitable solar radiation receivers, were exposed to combined proton and solar electromagnetic radiation. Each test sample was weighted, to simulate the tension on the polymer when it is stretched into near-planar shape while receiving solar radiation. Exposure rates up to 16 times that expected in Earth orbit were employed, to simulate near-sun solar sailing conditions. Sample appearance, elongation, and shrinkage were monitored, noted, and documented in situ. Thermosetting polyimides showed less degradation or visual change in appearance than thermoplastics.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-157322
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  • 149
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    The 40 KW of Solar Cell Modules for the Large Scale Production Task a Low Cost Silicon Solar Array Project (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Forty kilowatts of solar cell modules was produced in this program. This is equivalent to 4123 modules. The average power output per module was 9.7 watts at 16.5 volts, 60 C and 100 mW/sq cm. The peak production rate was 200 modules per week which is equal to 1.9 kW per week. This rate was sustained for over four and one-half months and is equivalent to 100 kW per year. This final report covers the solar cell module design, electrical and power performance, module preproduction environmental test results, production and shipping schedule, program summary, and delivery. A cost analysis section is written. Particular emphasis on the percentage of labor and material utilized in constructing a solar cell module is presented. Also included are cost reduction recommendations.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-157348 , DOE/JPL-95465-77/1
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  • 150
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    Automated array assembly (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general technology assessment and manufacturing cost analysis was presented. A near-term (1982) factory design is described, and the results of an experimental production study for the large-scale production of flat-panel silicon and solar-cell arrays are detailed.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-157317 , DOE/JPL-954352-77/4 , PRRL-77-CR-54
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  • 151
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    Design review package for the on-site monitor for solar heating and cooling systems (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance specification and verification matrix for the on-site monitor (OSM) is presented. The OSM is a portable device which, when connected to the Site Data Acquisition subsystem, allows readout of data on solar heating and cooling operational test sites.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150590
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  • 152
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    System design package for IBM system one: solar heating and domestic hot water (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report is a collation of documents and drawings that describe a prototype solar heating and hot water system using air as the collector fluid and a pebble bed for heat storage. The system was designed for installation into a single family dwelling. The description, performance specification, subsystem drawings, verification plan/procedure, and hazard analysis of the system was packaged for evaluation of the system with information sufficient to assemble a similar system.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150614
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  • 153
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    Effect of winglets on a first-generation jet transport wing. 1: Longitudinal aerodynamic characteristics of a semispan model at subsonic speeds (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of winglets and a simple wing-tip extension on the aerodynamic forces and moments and the flow-field cross flow velocity vectors behind the wing tip of a first generation jet transport wing were investigated in the Langley 8-foot transonic pressure tunnel using a semi-span model. The test was conducted at Mach numbers of 0.30, 0.70, 0.75, 0.78, and 0.80. At a Mach number of 0.30, the configurations were tested with combinations of leading- and trailing-edge flaps.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8473 , L-11354
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  • 154
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    Solar heating and cooling systems design and development (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development and delivery of eight prototype solar heating and cooling systems for installation and operational test was reported. Two heating and six heating and cooling units will be delivered for single family residences, multiple family residences and commercial applications.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150542 , F3437-QR-106
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  • 155
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    Indoor thermal performance evaluation of Daystar solar collector (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test procedures used and results obtained from a test program to obtain thermal performance data on a Daystar Model 21B, S/N 02210, Unit 2, liquid solar collector under simulated conditions are described. The test article is a flat plate solar collector using liquid as a heat transfer medium. The absorber plate is copper and coated with black paint. Between the tempered low iron glass and absorber plate is a polycarbonate trap used to suppress convective heat loss. The collector incorporates a convector heat dump panel to limit temperature excursions during stagnation. The following tests were conducted: (1) collector thermal efficiency; (2) collector time constant; (3) collector incident angle modifier; (4) collector heat loss coefficient; and (5) collector stagnation.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150511 , WYLE-TR-510-10-REV-A
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  • 156
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    Computer program for design and performance analysis of navigation-aid power systems. Program documentation. Volume 1: Software requirements document (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A computer program has been developed for designing and analyzing the performance of solar array/battery power systems for the U.S. Coast Guard Navigational Aids. This program is called the Design Synthesis/Performance Analysis (DSPA) Computer Program. The basic function of the Design Synthesis portion of the DSPA program is to evaluate functional and economic criteria to provide specifications for viable solar array/battery power systems. The basic function of the Performance Analysis portion of the DSPA program is to simulate the operation of solar array/battery power systems under specific loads and environmental conditions. This document establishes the software requirements for the DSPA computer program, discusses the processing that occurs within the program, and defines the necessary interfaces for operation.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: AD-A047925 , JPL-5040-27-VOL-1 , USCG-D-11-77-VOL-1 , CGR/DC-18/76-VOL-1
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  • 157
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    Thermal performance of MSFC hot air collectors under natural and simulated conditions (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The procedures used and the results obtained from an evaluation test program conducted to determine the thermal performance and structural characteristics of selected MSFC--designed hot air collectors under both real and simulated environmental conditions are described. Five collectors were tested in the three phased program. A series of outdoor tests were conducted to determine stagnation temperatures on a typical bright day and to determine each collector's ability to withstand these temperatures. Two of the collectors experienced structural deformation sufficient to eliminate them from the remainder of the test program. A series of outdoor tests to evaluate the thermal performance of collector S/N 10 under certain test conditions were performed followed by a series of indoor tests to evaluate the thermal performance of the collector under closely controlled simulated conditions.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150506 , WYLE-TR-531-05-REV-A
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  • 158
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    Mean Velocity, Turbulence Intensity and Turbulence Convection Velocity Measurements for a Convergent Nozzle in a Free Jet Wind Tunnel. Comprehensive Data Report (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of flight on the mean flow and turbulence properties of a 0.056m circular jet were determined in a free jet wind tunnel. The nozzle exit velocity was 122 m/sec, and the wind tunnel velocity was set at 0, 12, 37, and 61 m/sec. Measurements of flow properties including mean velocity, turbulence intensity and spectra, and eddy convection velocity were carried out using two linearized hot wire anemometers. This report contains the raw data and graphical presentations. The final technical report includes a description of the test facilities, test hardware, along with significant test results and conclusions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-135238 , PWA-5516
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  • 159
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    Technical and economic feasibility study of solar/fossil hybrid power systems (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results show that new hybrid systems utilizing fossil fuel augmentation of solar energy can provide significant capital and energy cost benefits when compared with solar thermal systems requiring thermal storage. These benefits accrue from a reduction of solar collection area that results from both the use of highly efficient gas and combined cycle energy conversion subsystems and elimination of the requirement for long-term energy storage subsystems. Technical feasibility and fuel savings benefits of solar hybrid retrofit to existing fossil-fired, gas and vapor cycle powerplants was confirmed; however, economic viability of steam cycle retrofit was found to be dependent on the thermodynamic and operational characteristics of the existing powerplant.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-73820 , E-9409
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  • 160
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    Indoor test for thermal performance evaluation of Lenox-Honeywell solar collector (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test procedures used and the test results obtained from an evaluation test program conducted on a double-covered liquid solar collector under simulated conditions are presented. The test article was a flat plate solar collector using liquid as the heat transfer medium. The absorber plate was steel with the copper tubes bonded on the upper surface. The plate was coated with black chrome with an absorptivity factor of .95 and emissivity factor of .12. A time constant test and incident angle modifier test were conducted to determine the transient effect and the incident angle effect on the collector.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150510 , WYLE-TR-531-09-REV-A
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  • 161
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    Collation of quarterly reports on air flat plate collectors (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The solar 2 air flat plate collectors are described. The development and fabrication of a prototype air flat plate collector subsystem containing 320 square feet of collector area are described. Three instrumented panels were completely assembled with glazing and insulation. Manufacture of the last seven prototype collectors was completed in October 1977.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150514
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  • 162
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    Comparison of solar system measured data for various sample rates (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of solar house data for sample rates of 50, 100, 250, 300, and 600 seconds were compared. The data considered for summer days were the heat incident on the collectors, the heat used by the air conditioner generator, and the heat used by the auxiliary heater. For winter days, the heat incident, the heat collected and the heat used by the heat exchanger were computed. These data were compared for different weather days such as clear days, partly cloudy days, cloudy days, and very cloudy days. Also, data for the integration of all these weather days were compared. The precentage differences for these data, using 50 second sample rate as a base, are also presented.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150496 , WYLE-TR-531-02
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  • 163
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    Thermal performance evaluation of Solar Energy Products Company (SEPCO) 'Soloron' collector tested outdoors (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test article, Model EF-212, Serial Nr. 002, is a single glazed collector with a nonselective absorber plate, using flowing air as the heat transfer medium. The absorber plate and box frame are aluminum and the insulation is one inch isocyanurate foam board with thermal conductivity of 0.11 (BTU/sq ft Hr0/ft.) The tests included the following. (1) time constant test, (2) collector efficiency test, (3) collector stagnation test, (4) incident angle modifier test, (5) load test, (6) weathering test, and (7) absorber plate optical properties test. The results of these tests are tabulated, graphed, or otherwise recorded.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150509 , WYLE-TR-531-08-REV-B
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    NASA Tech House (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The NASA Technology Utilization House, called Tech House, was designed and constructed at NASA's Langley Research Center in Hampton, Virginia, to demonstrate new technology that is available or will be available in the next several years and how the application of aerospace technology could help advance the homebuilding industry. Solar energy use, energy and water conservation, safety, security, and cost were major considerations in adapting the aerospace technology to the construction of Tech House.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-EP-149
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  • 165
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    Inhibitor analysis for a solar heating and cooling system (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study of potential corrosion inhibitors for the NASA solar heating and cooling system which uses aluminum solar panels is provided. Research consisted of testing using a dynamic corrosion system, along with an economic analysis of proposed corrosion inhibitors. Very good progress was made in finding a suitable inhibitor for the system.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150513
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  • 166
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    Indoor test for thermal performance evaluation of Libbey-Owens-Ford solar collector (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermal performance of a flat plate solar collector that uses liquid as the heat transfer medium was investigated under simulated conditions. The test conditions and thermal performance data obtained during the tests are presented in tabular form, as well as in graphs. Data obtained from a time constant test and incident angle modifier test, conducted to determine transient effect and the incident angle effect on the collector, are included.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150508 , WYLE-TR-531-07-REV-A
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  • 167
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    Verification test of the MSFC solar simulator using a Honeywell double-covered liquid solar collector (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Additional verification data to support the utilization of the MSFC Solar Simulator for testing solar collectors was obtained. The Honeywell double-covered liquid solar collector number 2 for which thermal performance data under natural outdoor conditions had been previously obtained was installed on the Solar Simulator and subjected to a series of eight tests under various conditions of wind flow rate. Although these test conditions were not absolutely identical to those of the outdoor tests, they are considered to be sufficiently representative to provide a basis for an accurate comparative analysis of the data recorded for both test programs.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150507 , WYLE-TR-531-06
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  • 168
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    Thermal performance of honeywell double covered liquid solar collector (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test procedures and results obtained during an evaluation test program to determine the outdoor performance characteristics of the Honeywell liquid solar collector are presented. The program was based on the thermal evaluation of a Honeywell double covered liquid solar collection. Initial plans included the simultaneous testing of a single covered Honeywell collector. During the initial testing, the single covered collector failed due to leakage; thus, testing continued on the double covered collector only. To better define the operating characteristics of the collector, several additional data points were obtained beyond those requested.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150505 , WYLE-TR-531-04
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  • 169
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    Performance evaluation of two black nickel and two black chrome solar collectors (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test program was based on the evaluation of four unique solar collectors described below: (1) black nickel collector surface with a desiccant drying bed, (2) black nickel collector surface without a desiccant drying bed, (3) black chrome collector surface with a dessicant drying bed, and (4) black chrome collector surface without a desiccant drying bed. The test program included three distinct phases: Initial performance evaluation, natural environmental aging, and post-aging performance evaluation. Results of Phase III testing conclusively indicated a higher normalized efficiency for Black Chrome surfaces when compared to Black Nickel.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150497 , WYLE-TR-531-3-REV-A
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  • 170
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    MSFC hot air collectors. Phase 1: Test report (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A development test program of 3 hot air flat plate solar collectors is described in detail. The pressure drop versus flow rate performance characteristics for these collectors, mounted in series, was determined under 14 different test conditions each of which was characterized by a unique combination of inlet air temperature and air flow rate. Characteristics of inlet, exit and transfer ducts of these collectors were also determined during this testing. The test results indicate that significant pressure drop occurs at air flow rates greater than 150 standard cubic feet per minute and this drop is not heavily dependent upon inlet air temperature; and inlet, exit and transfer duct characteristics differ sufficiently to suggest that system performance may be enhanced through careful design of each type of duct individually.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-150495 , WYLE-TR-531-1-REV-A
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  • 171
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    Synchronization of the DOE/NASA 100-kilowatt wind turbine generator with a large utility network (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The DOE/NASA 100 kilowatt wind turbine generator system was synchronized with a large utility network. The system equipments and procedures associated with the synchronization process were described. Time history traces of typical synchronizations were presented indicating that power and current transients resulting from the synchronizing procedure are limited to acceptable magnitudes.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-73861 , E-9450 , DOE/NASA/1028-77/10
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  • 172
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    Conceptual approach study of a 200 watt per kilogram solar array, phase 1 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two alternative designs were studied; one a retractable rollout design and the other a nonretractable foldout configuration. An end of life (EOL) power for either design of 0.79 beginning of life (BOL) is predicted based on one solar flare during a 3 year interplanetary mission. Both array configurations incorporate the features of flexible substrates and cover sheets. A power capacity of 10 kilowatt is achieved in a blanket area of 76 sq m with an area utilization factor of 0.8. A single array consists of two identical solar cell blankets deployed concurrently by a single, coilable longeron boom. An out of plane angle of 8-1/4 deg is maintained between the two blankets so that the inherent inplane stiffness of the blankets may be used to obtain out of plane stiffness. This V-stiffened design results in a 67% reduction in the stiffness requirement for the boom. Since boom mass scales with stiffness, a lower requirement on boom stiffness results in a lower mass for the boom. These solar arrays are designed to be compatible with the shuttle launch environment and shuttle cargo bay size limitations.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155614 , DOC-77SDS4207
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  • 173
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    Low cost solar energy collection system (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed, linear, ground-based primary reflector having an extended, curved sawtooth contoured surface covered with a metallized polymeric reflecting material, reflected solar energy to a movably supported collector that was kept at the concentrated line focus of the reflector primary. Efficient utilization leading to high temperatures from the reflected solar energy was obtained by cylindrical shaped secondary reflectors that directed off-angle energy to the absorber pipe.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 174
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    Two-dimensional wind tunnel test of an oscillating rotor airfoil, volume 2 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-16003.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2915 , D-210-11188-2
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  • 175
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    Transparent superstrate terrestrial solar cell module (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design, development, fabrication, and testing of the transparent solar cell module were examined. Cell performance and material process characteristics were determined by extensive tests and design modifications were made prior to preproduction fabrication. These tests included three cell submodules and two full size engineering modules. Along with hardware and test activity, engineering documentation was prepared and submitted.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155588 , ERDA/JPL-954653-77/1 , LMSC-D573729
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  • 176
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    Large area Czochralski silicon (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall cost effectiveness of the Czochralski process for producing large-area silicon was determined. The feasibility of growing several 12 cm diameter crystals sequentially at 12 cm/h during a furnace run and the subsequent slicing of the ingot using a multiblade slurry saw were investigated. The goal of the wafering process was a slice thickness of 0.25 mm with minimal kerf. A slice + kerf of 0.56 mm was achieved on 12 cm crystal using both 400 grit B4C and SiC abrasive slurries. Crystal growth experiments were performed at 12 cm diameter in a commercially available puller with both 10 and 12 kg melts. Several modifications to the puller hoz zone were required to achieve stable crystal growth over the entire crystal length and to prevent crystallinity loss a few centimeters down the crystal. The maximum practical growth rate for 12 cm crystal in this puller design was 10 cm/h, with 12 to 14 cm/h being the absolute maximum range at which melt freeze occurred.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155590 , ERDA/JPL-954475-77/4 , TI-03-77-23
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  • 177
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    Spraylon fluorocarbon encapsulation for silicon solar cell arrays (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A development program was performed for evaluating, modifying, and optimizing the Lockheed formulated liquid transparent filmforming Spraylon fluorocarbon protective coating for silicon solar cells and modules. The program objectives were designed to meet the requirements of the low-cost automated solar cell array fabrication process. As part of the study, a computer program was used to establish the limits of the safe working stress in the coated silicon solar cell array system under severe thermal shock.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155593 , LMSC-D558143
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  • 178
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    Solar array conceptual design for the Halley's Comet ion drive mission, phase 2 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Conceptual design studies were performed directed toward a high power, ultralightweight solar array, compatible with the requirements for the Halley's Comet Ion Drive Mission. A planar, rollup array design concept capable of producing 120 kW at 1 AU and 6 kW at 4.5 AU, and a concentrator, rollup array design concept capable of producing 60 kW at 1 AU and 15.5 kW at 4.5 AU evolved. Both arrays make maximum use of thin film, lightweight technology. The Halley's Comet spacecraft and mission requirements developed from preliminary definition to a more finalized and mature design. As solar array requirements were updated, conceptual design iterations were necessary to keep pace with the rapidly changing program objectives and goals. The Halley's Comet Mission program status and design approaches were reviewed and more realistic power requirements at 4.5 AU for the ion engines were established at the 12 to 16 kW range. This higher power necessitated a change from the planar array design to a concentrator array design in order to remain within suitable cost and weight objectives.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155594 , DOC-77SDS4243
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  • 179
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    Laser-zone growth in a Ribbon-To-Ribbon, RTR, process silicon sheet growth development for the large area silicon sheet task of the low cost silicon solar array project (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A ribbon-to-ribbon process was used for routine growth of samples for analysis and fabrication into solar cells. One lot of solar cells was completely evaluated: ribbon solar cell efficiencies averaged 9.23% with a highest efficiency of 11.7%. Spherical reflectors have demonstrated significant improvements in laser silicon coupling efficiencies. Material analyses were performed including silicon photovoltage and open circuit photovoltage diffusion length measurements, crystal morphology studies, modulus of rupture measurements, and annealing/gettering studies. An initial economic analysis was performed indicating that ribbon-to-ribbon add-on costs of $.10/watt might be expected in the early 1980's.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155586 , ERDA/JPL-954376-77/4
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  • 180
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    Approximate method for calculating free vibrations of a large-wind-turbine tower structure (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A set of ordinary differential equations were derived for a simplified structural dynamic lumped-mass model of a typical large-wind-turbine tower structure. Dunkerley's equation was used to arrive at a solution for the fundamental natural frequencies of the tower in bending and torsion. The ERDA-NASA 100-kW wind turbine tower structure was modeled, and the fundamental frequencies were determined by the simplified method described. The approximate fundamental natural frequencies for the tower agree within 18 percent with test data and predictions analyzed.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-73754 , ERDA/NASA-1028/77/12
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  • 181
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    Photovoltaic refrigeration application: Assessment of the near-term market (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This foreign and domestic market assessment was performed as part of the Tests and Applications Project being conducted by NASA-LeRC as part of the Department of Energy's (DOE) National Photovoltaic Program. One of the objectives of that program was to stimulate the demand for photovoltaic power systems so that appropriate markets would be developed in concert with the increasing photovoltaic production capacity. The refrigeration application represented a possible market for photovoltaics; hence, a brief survey of potential applications was conducted. Both refrigerators and refrigeration systems were considered in the assessment although the primary emphasis is on refrigerators of 9 cu ft of less. Three user sectors were examined: (1) government, (2) commercial/institutional, and (3) general public.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-73876 , E-9476 , DOE/NASA/1022-77/23
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  • 182
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    Two-dimensional wind tunnel test of an oscillating rotor airfoil, volume 1 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two dimensional wind tunnel test was conducted to obtain the quasisteady and unsteady characteristics of an advanced airfoil designed for helicopter rotor applications. Differential pressures were measured at 17 locations along the chord of the airfoil model. The airfoil motions were sinusoidal forced-pitch oscillations about the quarter chord at amplitudes varying from 2.5 to 10.0 degrees and at frequencies from 23 Hz to 90 Hz. The quasisteady tests were conducted at Mach numbers from 0.2 to 0.9, and the oscillatory tests between M = 0.2 and M = 0.7. At quasisteady conditions a limited number of drag measurements were made with a wake-traversing probe.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2914 , D210-11188-1-VOL-1
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  • 183
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    A generalized vortex lattice method for subsonic and supersonic flow applications (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: If the discrete vortex lattice is considered as an approximation to the surface-distributed vorticity, then the concept of the generalized principal part of an integral yields a residual term to the vorticity-induced velocity field. The proper incorporation of this term to the velocity field generated by the discrete vortex lines renders the present vortex lattice method valid for supersonic flow. Special techniques for simulating nonzero thickness lifting surfaces and fusiform bodies with vortex lattice elements are included. Thickness effects of wing-like components are simulated by a double (biplanar) vortex lattice layer, and fusiform bodies are represented by a vortex grid arranged on a series of concentrical cylindrical surfaces. The analysis of sideslip effects by the subject method is described. Numerical considerations peculiar to the application of these techniques are also discussed. The method has been implemented in a digital computer code. A users manual is included along with a complete FORTRAN compilation, an executed case, and conversion programs for transforming input for the NASA wave drag program.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2865 , LR-28112
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  • 184
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    Longitudinal aerodynamic characteristics at Mach 0.60 to 2.86 of a fighter configuration with strut braced wing (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made to determine the effects on longitudinal aerodynamic characteristics of utilizing struts to brace the wing to allow the wing thickness reduction on the LFAX-8 fighter configuration. Structural and load analysis indicated that the maximum airfoil thickness could be reduced from 4.5 to 3.1 percent with the strut brace concept. Wave drag theory indicated that reducing the wing maximum thickness from 4.5 percent to 3.1 percent would yield a significant reduction in zero-lift wave drag of about 28 percent at the design Mach number of 1.60. Strut arrangements designed and tested included, a single straight strut, a single swept strut, and a set of tandem straight struts. In addition, a wire of approximately the same cross sectional area replaced the single straight strut on one series of runs. The original LFAX-8 with the 4.5-percent-thick wing was retested to serve as a base line for this investigation.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1102 , L-11801
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  • 185
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    Projection of distributed-collector solar-thermal electric power plant economics to years 1990-2000 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary comparative evaluation of distributed-collector solar thermal power plants was undertaken by projecting power plant economics of selected systems to the 1990 to 2000 time frame. The selected systems include: (1) fixed orientation collectors with concentrating reflectors and vacuum tube absorbers, (2) one axis tracking linear concentrator including parabolic trough and variable slat designs, and (3) two axis tracking parabolic dish systems including concepts with small heat engine-electric generator assemblies at each focal point as well as approaches having steam generators at the focal point with pipeline collection to a central power conversion unit. Comparisons are presented primarily in terms of energy cost and capital cost over a wide range of operating load factors. Sensitvity of energy costs for a range of efficiency and cost of major subsystems/components is presented to delineate critical technological development needs.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155427 , JPL-PUB-77-79
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  • 186
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    Solar cell radiation handbook (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Solar cell theory cells are manufactured, and how they are modeled mathematically is reviewed. The interaction of energetic charged particle radiation with solar cells is discussed in detail and the concept of 1 MeV equivalent electron fluence is introduced. The space radiation environment is described and methods of calculating equivalent fluences for the space environment are developed. A computer program was written to perform the equivalent fluence calculations and a FORTRAN listing of the program is included. Finally, an extensive body of data detailing the degradation of solar cell electrical parameters as a function of 1 MeV electron fluence is presented.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155554 , JPL-PUB-77-56
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  • 187
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    A fixed tilt solar collector employing reversible vee-trough reflectors and vacuum tube receivers for solar heating and cooling systems (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The usefulness of vee-trough concentrators in improving the efficiency and reducing the cost of collectors assembled from evacuated tube receivers was studied in the vee-trough/vacuum tube collector (VTVTC) project. The VTVTC was analyzed rigorously and various mathematical models were developed to calculate the optical performance of the vee-trough concentrator and the thermal performance of the evacuated tube receiver. A test bed was constructed to verify the mathematical analyses and compare reflectors made out of glass, Alzak and aluminized FEP Teflon. Tests were run at temperatures ranging from 95 to 180 C. Vee-trough collector efficiencies of 35 to 40% were observed at an operating temperature of about 175 C. Test results compared well with the calculated values. Predicted daily useful heat collection and efficiency values are presented for a year's duration of operation temperatures ranging from 65 to 230 C. Estimated collector costs and resulting thermal energy costs are presented. Analytical and experimental results are discussed along with a complete economic evaluation.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155426 , JPL-PUB-77-78
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  • 188
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    Study of the potential for improving the economics of hydrogen liquefaction through the use of centrifugal compressors and the addition of a heavy water plant (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approach to the liquefaction of hydrogen was developed which permits the application of standard centrifugal compressors in place of reciprocating machines. A second fluid, such as propane, is added to the hydrogen prior to compression to form a mixture having a molecular weight much greater than that of hydrogen alone, so that a standard centrifugal compressor can be used. After compression, the mixture is cooled to cryogenic temperature levels where the propane condenses out of the mixture and is separated as a liquid. Since a small amount of deuterium is produced during hydrogen liquefaction, the potential of recovering deuterium and selling it as a co-product was investigated. Deuterium, in the form of heavy water, can be used in certain nuclear reactors as a neutron moderator to reduce the neutron velocity and enhance the probability of neutron collision with uranium nucleii.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-145282
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  • 189
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    Solar heating system (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A system is disclosed for using solar energy to heat the interior of a structure. The system utilizes a low cost solar collector to heat a recirculating air mass which then flows through a series of interconnected ducts and passageways without the use of exterior fans or blowers. Heat is transferred from the air mass to the structure's interior and the air mass is then reheated.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 190
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    Aerodynamic characteristics of a monoplanar missile concept with bodies of circular and elliptical cross sections (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic characteristics of a low-drag missile concept with a body of circular cross section were compared to one with a body of 3:1 elliptical cross section, the bodies having identical cross section area distributions. The concepts were of monowing design with constant wing span. Tail surfaces were located flush at the body base with plus or minus 30 deg dihedral. Wind tunnel tests were performed at Mach numbers from 0.5 to 4.63 and at angles of attack from about -5 deg to 28 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74079 , L-11423
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  • 191
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    Improvement of maneuver aerodynamics by spanwise blowing (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Spanwise blowing was used to test a generalized wind-tunnel model to investigate component concepts in order to provide improved maneuver characteristics for advanced fighter aircraft. Primary emphasis was placed on performance, stability, and control at high angles of attack and subsonic speeds. Test data were obtained in the Langley high speed 7 by 10 foot tunnel at free stream Mach numbers up to 0.50 for a range of model angles of attack, jet momentum coefficients, and leading and trailing edge flap deflection angles. Spanwise blowing on a 44 deg swept trapezoidal wing resulted in leading edge vortex enhancement with subsequent large vortex induced lift increments and drag polar improvements at the higher angles of attack. Small deflections of a leading edge flap delayed these lift and drag benefits to higher angles of attack. In addition, blowing was more effective at higher Mach numbers. Spanwise blowing in conjunction with a deflected trailing edge flap resulted in lift and drag benefits that exceeded the summation of the effects of each high lift device acting alone. Asymmetric blowing was an effective lateral control device at the higher angles of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1065 , L-11642
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  • 192
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    Solar energy meter (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An instrument was developed to continually integrate the energy available in incident light on a specifically oriented surface. The unit was designed for outdoor use in remote locations and is capable of operation over a temperature range of -20 to +60 C with good accuracy. The unit is weather resistant, requires low power, has a high input impedance, is inexpensive, and has a visual readout and an analog output for recording.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-73791 , E-9358 , ERDA/NASA-1022/77/21
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  • 193
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    Anion exchange membranes for electrochemical oxidation-reduction energy storage system (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Oxidation-reduction couples in concentrated solutions separated by appropriate ion selective membranes were considered as an attractive approach to bulk electrical energy storage. A key problem is the development of the membrane. Several promising types of anionic membranes are discussed which were developed and evaluated for redox energy storage systems. The copolymers of ethyleneglycoldimethacrylate with either 2-vinylpyridine or vinylbenzl chloride gave stable resistance values compared to the copolymer of vinylbenzlchloride and divinylbenzene which served as the baseline membrane. A polyvinylchloride film aminated with tetraethylenepentamine had a low resistance but a high ion transfer rate. A slurry coated vinylpyridine had the lowest ion transfer rate. All these membranes functioned well in laboratory cells at ambient temperatures with the acidic chloride oxidant/reductant system, Fe 3, Fe 2/Ti 3, Ti 4.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-73751 , ERDA/NASA-1002/77/2 , E-9222
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 194
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    Multi-cell battery protection system (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A multi-cell battery protection system is described wherein each cell has its own individual protective circuit. The protective circuits consist of a solid state comparator unit and a high current switching device such as a relay. The comparator units each continuously monitor the associated cell and when the cell voltage either exceeds a predetermined high level or falls below a predetermined low level, the relay is actuated whereby a bypass circuit is completed across the cell thereby effectively removing the cell from the series of cells.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 195
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    Aerodynamic characteristics of a small-scale straight and swept-back wing with knee-blown jet flaps (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two sting-mounted, 50.8 cm (20 in.) span, knee-blown, jet-flap models were tested in a large (2.1- by 2.5-m (7- by 10-ft) subsonic wind tunnel. A straight- and swept-wing model were tested with fixed flap deflection with various combinations of full-span leading-edge slats. The swept-wing model was also tested with wing tip extensions. Data were taken at angles-of-attack between 0 deg and 40 deg, at dynamic pressures between 143.6 N/sq m (3 lb/sq ft) and 239.4 N/sq m (5 lb/sq ft), and at Reynolds numbers (based on wing chord) ranging from 100,000 to 132,000. Jet flap momentum blowing coefficients up to 10 were used. Lift, drag, and pitching-moment coefficients, and exit flow profiles for the flap blowing are presented in graphical form without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78427 , A-7161
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 196
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    Advanced Thermionic Technology Program (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Topics include surface studies (surface theory, basic surface experiments, and activation chamber experiments); plasma studies (converter theory and enhanced mode conversion experiments); and component development (low temperature conversion experiments, high efficiency conversion experiments, and hot shell development).
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155299 , COO-3056-23 , TE-4217/4220-123-77 , PR-22
    Format: application/pdf
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  • 197
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    Solar energy bibliography (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Listings are provided of technical briefs, reports, and papers pertaining to research being performed in the field of solar energy.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-X-73398
    Format: application/pdf
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  • 198
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    Candidate locations for SPS rectifying antennas (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of placing 120 Satellite Power System (SPS) rectifying antenna (rectenna) sites across the U.S. was studied. An initial attempt is made to put two land sites in each state using several land site selection criteria. When only 69 land sites are located, it is decided to put the remaining sites in the sea and sea site selection criteria are identified. An estimated projection of electrical demand distribution for the year 2000 is then used to determine the distribution of these sites along the Pacific, Atlantic, and Gulf Coasts. A methodology for distributing rectenna sites across the country and for fine-tuning exact locations is developed, and recommendations on rectenna design and operations are made.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-78146
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 199
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    Parametric study of rock pile thermal storage for solar heating and cooling phase 1 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test data and an analysis were presented, of heat transfer characteristics of a solar thermal energy storage bed utilizing water filled cans as the energy storage medium. An attempt was made to optimize can size, can arrangement, and bed flow rates by experimental and analytical means. Liquid filled cans, as storage media, utilize benefits of both solids like rocks, and liquids like water. It was found that this combination of solid and liquid media shows unique heat transfer and heat content characteristics and is well suited for use with solar air systems for space and hot water heating. An extensive parametric study was made of heat transfer characteristics of rocks, of other solids, and of solid containers filled with liquids.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-155336
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 200
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    Radiation tests of SEP solar cells (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Solar cells specially designed for Solar Electric Propulsion (SEP) were tested with radiation fluences up to 10 to the 12th power protons having energies of 1.5, 1.0, and 0.5 MeV, and with fluences up to 10 to the 16th power electrons having 1.0 MeV energy. Spectrolab cells having a back-surface field were also irradiated with the same particles and fluences. Cell performances are described by curves in which normalized and absolute values of maximum power, maximum-power voltage, short-circuit current, and open-circuit voltage are plotted as a function of fluence.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Res. Center Solar Cell High Efficiency and Radiation Damage; p 187-205
    Format: text
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