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  • Organic Chemistry  (694)
  • AERODYNAMICS  (381)
  • Life and Medical Sciences  (370)
  • Aircraft Propulsion and Power
  • INSTRUMENTATION AND PHOTOGRAPHY
  • 1980-1984
  • 1975-1979  (1,680)
  • 1960-1964
  • 1950-1954
  • 1978  (1,680)
Collection
Keywords
Publisher
Years
  • 1980-1984
  • 1975-1979  (1,680)
  • 1960-1964
  • 1950-1954
Year
  • 1
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    A parametric experimental study of the slotted-wall boundary condition (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An experimental study of slotted upper and lower walls in a two dimensional transonic wind tunnel with solid sidewalls is reported. Results are presented for several slot spacings and slot openness ratios. The experimental data were pressure measurements which were made on an airfoil model and on a sidewall near one of the slotted walls. The slotted-wall boundary condition coefficient, which related the pressure and streamline curvature near the wall, was determined from the wall pressure measurements. The measured wall-induced interference was correlated with the experimental values for the boundary condition coefficient. This correlation was compared with theory.
    Keywords: AERODYNAMICS
    Type: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 459-471
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  • 2
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    Holography and LDV techniques, their status and use in airfoil research (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The measurement capabilities of laser velocimetry and holographic interferometry in transonic airfoil testing were demonstrated. Presented are representative results obtained with these two nonintrusive techniques on a 15.24 cm chord airfoil section. These results include the density field about the airfoil, flow angles in the inviscid flow and viscous flow properties including the turbulent Reynolds stresses. The accuracies of the density fields obtained by interferometry were verified from comparisons with surface pressure and laser velocimeter measurements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 589-599
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  • 3
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    A procedure for analyzing transonic flow over harmonically oscillating airfoils (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Finite difference procedures were successfully used to solve the steady transonic flow about airfoils and appear to provide a practical means for calculating the corresponding unsteady flow. The purpose of the paper is to describe a finite difference procedure derived from the equations for the potential flow by assuming small perturbations and harmonic motion. The velocity potential is divided into steady and unsteady parts, and the resulting unsteady equation is linearized on the basis of small amplitudes of oscillation. The steady velocity potential, which must be calculated first, is described by the classical nonlinear transonic differential equation.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 657-670
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  • 4
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    Section drag coefficients from pressure probe transverses of a wing wake at low speeds (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An in-flight wing wake section drag investigation was conducted using traversing pitot and static probes. The primary objective was to develop measurement techniques and improve the accuracy of in-flight wing profile drag measurements for low values of dynamic pressure and Reynolds number. Data were obtained on a sailplane for speeds from about 40 knots to 125 knots at chord Reynolds numbers between 1,000,000 and 3,000,000. Tests were conducted with zero flap deflection, deflected flaps, and various degrees of surface roughness, and for smooth and rough atmospheric conditions. Several techniques were used to increase data reliability and to minimize certain bias errors. A discussion of the effects of a total pressure probe in a pressure gradient, and the effects of discrete turbulence levels, on the data presented and other experimental results is also included.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 601-621
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  • 5
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    Some calculations of transonic potential flow for the NACA 64A006 airfoil with oscillating flap (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A method for calculating the transonic flow over steady and oscillating airfoils was developed by Isogai. It solves the full potential equation with a semi-implicit, time-marching, finite difference technique. Steady flow solutions are obtained from time asymptotic solutions for a steady airfoil. Corresponding oscillatory solutions are obtained by initiating an oscillation and marching in time for several cycles until a converged periodic solution is achieved. In this paper the method is described in general terms, and results are compared with experimental data for both steady flow and for oscillations at several values of reduced frequency. Good agreement for static pressures is shown for subcritical speeds, with increasing deviation as Mach number is increased into the supercritical speed range. Fair agreement with experiment was obtained at high reduced frequencies with larger deviations at low reduced frequencies.
    Keywords: AERODYNAMICS
    Type: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 689-700
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  • 6
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    Applications of dynamic measurement techniques to wind-tunnel testing (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The uses of laser Doppler velocimeter, hot wire, and surface hot film techniques in the study of turbulent flows are described, and data obtained in compressible flows are discussed. Applications are illustrated with measurements of wind tunnel freestream turbulence characteristics and with data obtained in transitional, turbulent, and separated shear flows. A new method which was developed for the study of time dependent and unsteady turbulent flows is also presented.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 571-588
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  • 7
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    Instrumentation, techniques and data reduction associated with airfoil testing programs at Wichita State University (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Two dimensional airfoil testing was conducted at the Wichita State University Beech Wind Tunnel for a number of years. The instrumentation developed and adapted during this period of testing for determination of flow fields along with traversing mechanisms for these probes are discussed. In addition, some of the techniques used to account for interference effects associated with the apparatus used for this two dimensional testing are presented. The application of a minicomputer to the data reduction and presentation is discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 539-558
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  • 8
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    The Temperature Humidity Infrared Radiometer (THIR) subsystem (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The infrared radiation from the earth in two spectral bands during both day and night portions of the orbit is measured. Pictures of cloud cover, three dimensional mappings of cloud cover, temperature mappings of clouds, land, and ocean surface, cirrus cloud content, atmospheric contamination, and relative humidity are provided.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Nimbus 7 User's Guide 247-262 (SEE N79-20148 11-12)
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  • 9
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    The Scanning Multichannel Microwave Radiometer (SMMR) experiment (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Ocean momentum and energy transfer parameters on a nearly all weather operational basis are obtained and used. The winds, water vapor, liquid water content, temperature, and mean cloud droplet size are derived from low altitude parameters.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Nimbus 7 User's Guide; p 213-246
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  • 10
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    The Coastal Zone Color Scanner (CZCS) experiment (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The CZCS is used to map chlorophyll concentration, sediment distribution, gelbstroffe concentration, and temperature of coastal waters and the open ocean. The data processing techniques used to enhance contrasts over the ocean and to remove the effect of the backscattered atmosphere are presented. The multi-channel scanning radiometer of CZCS is described. The content of water is determined primarily by the CZCS measurement.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center The Nimbus 7 User's Guide; p 19-32
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  • 11
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    DSN water vapor radiometer development: Recent work, 1978 (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: A water vapor radiometer (WVR) was developed that measures the atmospheric noise temperature at two different frequencies near 22 GHz. These noise temperature are used in empirical-theoretical equations that yield tropospheric range delay, in centimeters, through the atmosphere along the beam of the WVR. This range correction is then applied, as needed, to measurements concerning spacecraft range and to VLBI baseline determinations. The WVR design and calibration techniques are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Deep Space Network; p 129-135
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  • 12
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    Frequency selection and calibration of a water vapor radiometer (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The calibration coefficients of existing water vapor radiometers are dependent upon meteorology profiles. This is shown to be due mainly to incorrect frequency pairs. By properly selecting an optimum frequency pair, the dependency can be reduced to a relatively small amount which can be handily adjusted by surface measurement alone. Hence, a universal calibration equation is applicable to all environmental conditions - site, seasonal and diurnal variations. Optimum frequency pairs are systematically searched. Error analysis indicates that calibration for the water vapor phase delay accurate to less than 2 cm is possible at all elevation angles greater than 15 degrees.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Deep Space Network; p 67-81
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  • 13
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    Preliminary design work on a DSN VLBI correlator (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The Deep Space Network is in the process of fielding high-density digital instrumentation recorders for support of the Pioneer Venus 1978 entry experiment and other related tasks. It has long been obvious that these recorders would also serve well as the recording medium for very long base interferometry (VLBI) experiments with relatively weak radio sources, provided that a suitable correlation processor for these tape recordings could be established. The overall design and current status of a VLBI correlator designed to mate with these tape recorders are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Deep Space Network; p 90-98
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  • 14
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    Development of a drift-correction procedure for a photoelectric spectrometer (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A technique has been developed to automatically correct for drifts in the radiometric sensitivity of the detector channels in a direct-reading emission spectrometer. The method utilizes a 1000 W tungsten-halogen reference lamp to illuminate the detectors through the same optical path as that traversed during the analysis of the sample. Detector channel responses to the light are compared to those for the same light intensity at the time of analytical calibration. This corrects for the drift. It is noted that with the exception of positioning the lamp, the procedure is fully automatic.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Spectroscopy; 32; Jan
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  • 15
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    Gamma ray spectroscopy in astrophysics: Future role of scintillation detectors (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The future role of conventional scintillation detector telescopes for line gamma-ray astronomy is discussed. Although the energy resolution of the germanium detectors now being used by several groups is clearly desirable, the larger effective areas and higher efficiencies available with scintillation detectors is advantageous for many observations. This is particularly true for those observations of astrophysical phenomena where significant line broadening is expected.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 438-449
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  • 16
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    Aerodynamic effects (1978)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The tethered satellite concept provides an ideal platform for the study of the interaction of the atmosphere with satellites of various shapes and surfaces under a wide range of flow conditions. From experiments which would measure the drag, lift, and torque acting on the tethered satellite, important information could be obtained which would have application to satellite lifetime prediction, determination of properties of the upper atmosphere, and scientific information on the interaction of high speed molecules with surfaces (the gas surface interaction). These experiments using the tethered satellite concept are described and would measure the following variables: angle of attack, surface roughness, and flow properties.
    Keywords: AERODYNAMICS
    Type: UAH(NASA Workshop on the Use of a Tethered Satellite System; p 151-155
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  • 17
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    Prospects for computational aerodynamics (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The integral representations approach, for the solution of the Navier-Stokes equations is discussed as well as experience in its development and in applying available finite-difference and finite-element techniques to the treatment of three-dimensional problems, and the computation of turbulent flow. The magnitude of efforts required to develop turbulence models and three-dimensional algorithms indicates that the computational fluid dynamics research must have a broad base. Broader access to modern computing facilities that are in existence within NASA should be promoted for active researchers not directly affiliated with that agency.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 221-227
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  • 18
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    Modeling of the Reynolds stresses (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: In their most general form, the Reynolds averaged conservation equations result from ensemble or time averages of the instantaneous Navier-Stokes equations or their compressible counterparts. For these averaging processes to be consistent, the averaging time period must exceed the periods identified with the largest time scales of the turbulence, and yet be shorter than the characteristic times of the flow field. With these equations long period variations in the flow fields are deterministic, provided initial conditions are known. The average dependent variables are sufficiently smooth to be resolvable by finite difference techniques consistent with the size and speed of modern computers.
    Keywords: AERODYNAMICS
    Type: Future Computer Requirements for Computational Aerodynamics; p 239-247
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  • 19
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    Computational aerodynamics and the numerical aerodynamic simulation facility (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Technical and economic reasons for accelerating the maturation of the discipline of computational aerodynamics include the cost of conducting the experiments required to provide the empirical data base for new aeronautical vehicles and the limitations in test facilities (Reynolds number, wall and support interferences, aeroelastic distortions, real-gas effects, etc.) for simulating the full-scale vehicle environment. General purpose computers do not have the necessary capability for the next stage of development. Solution of the three dimensional Reynolds averaged Naiver-Stokes equations in a short time to be practical for design purposes will require 40 times the power of current supercomputers. However, it is feasible to construct a special purpose processor that will meet these requirements to enhance the nation's aerodynamic design capability in the 1980's.
    Keywords: AERODYNAMICS
    Type: Future Computer Requirements for Computational Aerodynamics; p 5-30
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  • 20
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    Carbon vaporization into a nonequilibrium, stagnation-point boundary layer (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The heat transfer to the stagnation point of an ablating carbonaceous heat shield, where both the gas-phase boundary layer and the heterogeneous surface reactions are not in chemical equilibrium, is examined. Specifically, the nonequilibrium changes in the mass fraction profiles of carbon species calculated for frozen flow are studied. A set of equations describing the steady-state, nonequilibrium laminar boundary layer in the axisymmetric stagnation region, over an ablating graphite surface, is solved, with allowance for the effects of finite rate of carbon vaporization.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 16; July 197
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  • 21
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    Perturbations in two- and three-dimensional transonic flows (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The difficulty of treating the perturbation of transonic flow, during which shock waves change position, can be overcome by using a distorted coordinate system in which the locations of all shock waves do not change; the distortion is found as part of the solution. This device leads to a relation that allows a range of flows, with differing shock locations, to be related algebraically to two known 'calibration' flows. Results for flows around finite wings, including those with multiple, intersecting shock waves, are presented. A typical computing time for such examples is 0.3 sec on a CDC 7600 computer.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 16; July 197
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  • 22
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    Capabilities of germanium detectors (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The gamma ray detection efficiency and energy resolution of germanium detectors is reviewed. A general sensitivity equation for gamma-ray detectors is presented and calculated sensitvity curves are shown for a large volume balloon-borne spectrometer using germanium detectors. Improvement anticipated from a planned satellite experiment using germanium detectors is discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 450-461
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  • 23
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    Numerical solution for supersonic flow near the trailing edge of a flat plate (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: In the present study, problems of laminar and turbulent two-dimensional flow of a viscous compressible fluid near the trailing edge of a thin flat plate are considered. The complete set of Navier-Stokes equations is solved by the finite-difference method of MacCormack (MacCormack and Baldwin, 1975). It is an explicit, predictor-corrector, time-splitting method of second order acuracy. The computational mesh employed has sufficient resolution for all the characteristic lengths suggested by theory. In the laminar case, the present results are compared with the triple deck solution of Daniels (1974). This comparison indicates that the asymptotic triple deck theory for supersonic trailing edge flow is accurate within five percent for Reynolds numbers greater than 1000. In the turbulent case, the Prandtl-Van Driest-Clauser algebraic eddy viscosity model is used. The numerical results show that the region of upstream influence is approximately of the order of the boundary layer thickness. The solutions for skin-friction, pressure and wake center-line velocity are presented.
    Keywords: AERODYNAMICS
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  • 24
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    Development of 1366 K /2000 F/ strain sensor and biaxial strain transducer for use to 1033 K /1400 F/ (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 25
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    Infra-red measurements of stratospheric composition. I - The balloon instrument and water vapour measurements (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The design and construction of a balloon-borne instrument for remote-sensing of stratospheric composition is described. Thermal emission from the constituents is detected and the spectral selectivity of the instrument is tailored to a specific gas by the use of a cell of the same gas in the optical path of the radiometer. The pressure of the gas in the cell is cycled and the resultant transmission function is shown to be highly selective to radiation from the same gas in the atmosphere. The first flight of the instrument and the retrieval of a water vapour profile in the range 15-40 km is described.
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  • 26
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    Unsteady vortical and entropic distortions of potential flows round arbitrary obstacles (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The analysis concerns the alterations produced when small amplitude disturbances, including entropy and vorticity disturbances, are imposed on steady potential flows. For the most general nonacoustic incident distortion field that can be imposed on the uniform upstream flow, it is shown that the perturbation velocity at any point of the resulting unsteady compressible and vortical flow consists of a part that is a known function of the imposed upstream distortion field and the mean flow variables and a potential part that can be found by solving a linear inhomogeneous wave equation with a dipole-type source term whose strength is a known function of the imposed upstream distortion field. The theory is applied to the unsteady flow past a corner, and a closed-form analytical solution is found.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 89; Dec. 13
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  • 27
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    Reynolds number influence on leeside flowfields (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Experimental results on the Reynolds number influence on the leeside flowfield of planar delta wings at supersonic speeds are presented. Wind tunnel experiments on two delta wing models with straight and sharp leading edges at freestream Mach number of 2.5 and 3.5 and angle of attack between 1 deg and 12.5 deg were carried out. The cross-sectional shape was triangular and the relative height was 0.25. The flow types investigated were to the left and right of the Stanbrook-Squire boundary. Under leading-edge separation conditions, the vortex position and intensity, and thus the suction pressure, vary with Re while the flow type remains nearly unchanged. In the region of separation with embedded shock, Re affects not only the shape of the separation bubble and pressure level near the leading edge but also the type of flow. At sufficiently high Re the flow type of separation with shock changes to one with shock-induced separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 16; Dec. 197
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  • 28
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    Unsteady flow in a supersonic cascade with subsonic leading-edge locus (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Linearized theory is used to predict the unsteady flow in a supersonic cascade with subsonic axial flow velocity. A closed-form analytical solution is obtained by using a double application of the Wiener-Hopf technique. Although numerical and semianalytical solutions of this problem have already appeared in the literature, this paper contains the first completely analytical solution. It has been stated in the literature that the blade source should vanish at the infinite duct resonance condition. The present analysis shows that this does not occur. This apparent discrepancy is explained in the paper.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 16; Dec. 197
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  • 29
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    Detected noise levels guide radiometer design (1978)
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    Publication Date: 2011-08-17
    Description: A survey of component demands and design techniques for radiometers is presented. The design of a typical radiometer is traced from the antenna through the video and data-collection stages. Key design equations are given. An example is considered that shows how IF amplifier gain must be chosen to mask video noise. The influence of front-end losses on back-end design is studied.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: MicroWaves; 17; Sept
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  • 30
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    Visualization of relaminarizing flows (1978)
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    Publication Date: 2011-08-17
    Description: The experiments described in the present paper provided conclusive evidence for the feasibility of achieving reverse transition by several different mechanisms. Turbulent-to-laminar transition in water was visualized by injection of purple and green dyes. Air flows were visualized by colored schlieren photography.
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  • 31
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    Coded aperture imaging with uniformly redundant arrays (1978)
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    Publication Date: 2011-08-17
    Description: The paper discusses uniformly redundant arrays (URA) as applied to coded aperture imaging. The URA system offers the high-transmission characteristics of random arrays as well as a flat sidelobe advantage. The high-transmission yields the imaging of very low-intensity sources and the flat sidelobes provide the suppression of inherent noise which obscures low-contrast sources. Simulations have shown that the URA with shot and background noise produces a better reconstructed object than random arrays without shot or background noise. The URA also offers an arrangement which involves a mosaic of basic URA patterns forming a circular correlation of the object on the picture plane. Thus the information needed to reconstruct the object is contained in an area equal to that of the basic aperture pattern. This smaller required detector is important in applications including X-ray astronomy.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 17; Feb. 1
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  • 32
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    Inlet boundary-layer shapes on four aircraft forebodies at Mach 6 (1978)
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    Publication Date: 2011-08-17
    Description: Boundary-layer shape measurements at the engine inlet on four different hypersonic aircraft forebody designs (with no engine on the forebody) are reported. The measurements provide a qualitative assessment of the effectiveness of various forebody geometries as engine inlet precompression surfaces. The designs, tested in a hypersonic tunnel at Mach 6 and a nominal freestream Reynolds number of 30,500,000, included a semiconical forebody, a configuration similar to a slab delta wing, a conical nose blended into a flat surface, and a conical, complex forebody shape. Boundary layer height as a function of forebody compression is shown for each design.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 15; Jan. 197
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  • 33
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    Design criteria for reflection polarizers and analyzers in the vacuum ultraviolet (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Reflection polarizers and analyzers for the extreme UV spectral region are discussed. The conditions for optimum polarization are presented, and the polarization characteristics of a number of metal coatings, including gold and some of the platinum metals, are given. The performance of three- and four-mirror polarizers, using these metal coatings, is discussed. The properties required of a polarization analyzer are presented, and the performance of single and three- and four-reflection analyzers are discussed in terms of the optical properties of coating materials that might be useful for analyzers.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 17; Apr. 15
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  • 34
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    Upconversion of broadband infrared spectra (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An experimental device successfully upconverts IR radiation in the 3.2-5.0 micron wavelength range simultaneously to visible light at 0.80-0.88 microns, while preserving frequency coding and is thus applicable to IR spectroscopy. The 1.8-micron bandwidth of IR radiation that is upconverted without temperature or phase match tuning is the largest yet reported. The over-all system quantum efficiency of the upconverter/spectrometer system is 0.01% and could be improved to 0.4%.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 17; Apr. 15
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    A 10 micron laser heterodyne spectrometer for remote detection of trace gases (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Infrared heterodyne spectroscopy provides a means of measuring the intensity profiles of individual rotation-vibration spectral lines with high sensitivity. Considerable effort has been expended on optimizing these instruments for remote measurements of gases in planetary atmospheres with the result that present-generation spectrometers are beginning to provide new and startling results on the planets. The fundamental principles of laser heterodyne spectroscopy are discussed. Detailed considerations of the optical design and the electronic design of the spectral-line receiver are given. Representative results obtained with this spectrometer are discussed, including precision frequency measurements of NH3 (nu-2) lines, detection of auroral emission from Jupiter, and measurements of terrestrial O3 and CO2.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 17; Jan
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  • 36
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    Notes on the transonic indicial method (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The indicial method for calculating flutter derivatives for two-dimensional airfoils at transonic speeds is discussed, with particular attention given to the effect of a moving shock on the flow variables in the indicial method. An expression for the pressure coefficient is developed on the basis of an explicit treatment of the shock motion; the pressure distribution may then be calculated for general oscillations through use of the indicial method. Explicit inclusion of the shock motion is not necessary if only the lift and pitching moment coefficients are desired.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 16; June 197
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  • 37
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    Ultraviolet spectrophotometer for measuring columnar atmospheric ozone from aircraft (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An ultraviolet spectrophotometer (UVS) to measure downward solar fluxes from an aircraft or other high altitude platform is described. The UVS uses an ultraviolet diffuser to obtain large angular response with no aiming requirement, a twelve-position filter wheel with narrow (2-nm) and broad (20-nm) bandpass filters, and an ultraviolet photodiode. The columnar atmospheric ozone above the UVS (aircraft) is calculated from the ratios of the measured ultraviolet fluxes. Comparison with some Dobson station measurements gives agreement to 2%. Some UVS measured ozone profiles over the Pacific Ocean for November 1976 are shown to illustrate the instrument's performance.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 17; May 15
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  • 38
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    A spectroradiometer for airborne remote sensing (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A remote sensing system for use in light aircraft is discussed with attention to its applications in measuring geologic zones of alteration, vegetation canopies, and the spectral properties of water bodies. A parallel electro-optical input spectroradiometer configuration with 500 channels operating in the 400-1100 nm region is described. A resolution of 18 meters square from an altitude of 600 m at 200 kmh is obtained with 4-digit spectral radiance data at 2.5 spectra/sec on a 9-track tape in computer compatible format.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Photogrammetric Engineering and Remote Sensing; 44; Apr. 197
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  • 39
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    Comparison between photographic and photoelectric measurements of the solar aureole almucantar radiance (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 17; July 1
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  • 40
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    Electronic heterodyne recording and processing of optical holograms using phase modulated reference waves (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The use of a phase-modulated reference wave for the electronic heterodyne recording and processing of a hologram is described. Heterodyne recording is used to eliminate the self-interference terms of a hologram and to create a Leith-Upatnieks hologram with coaxial object and reference waves. Phase modulation is also shown to be the foundation of a multiple-view hologram system. When combined with hologram scale transformations, heterodyne recording is the key to general optical processing. Spatial filtering is treated as an example.
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  • 41
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    Effects of accumulated film layers on the accuracy of quartz film thickness monitors (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The effect of accumulation layers on the accuracy of quartz thin-film thickness monitors is evaluated. Use of an expanded plane wave ultrasonic propagation theory correctly accounts for observed experimental data. The magnitude of the maximum errors calculated for simply reversing the order of a series of aluminum gold deposits is on the order of 5%. If one totally neglects intervening layers, multiple film propagation and nonlinearity can produce errors greater than 50%.
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  • 42
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    Stratospheric trace gas sampling with chemical absorption filters (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Recent interest in stratospheric chemistry, sparked in part by the suggested roles of atomic chlorine (Cl) and nitrogen oxides (NOx) in the catalytic destruction of ozone (O3), has made sampling and measurement of trace constituents above the tropopause highly desirable. An ongoing research program in the In Situ Studies Project at the National Center for Atmospheric Research carries out aircraft and balloon-borne stratospheric chemical sampling at regular intervals by using chemically impregnated filters to collect particles and reactive gases.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Atmospheric Technology; Spring 1
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  • 43
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    Improved apparatus for trapped radical and other studies down to 1.5 K (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A Dewar system and associated equipment for electron paramagnetic resonance (EPR) studies of trapped free radicals and other optical or irradiation experiments are described. The apparatus is capable of reaching a temperature of 1.5 K and transporting on the order of 20 W per K temperature gradient; its principal advantages are for use at pumped cryogen temperatures and for experiments with large heat inputs. Two versions of the apparatus are discussed, one of which is designed for EPR in a rectangular cavity operating in a TE(102) mode and another in which EPR is performed in a cylindrical microwave cavity.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 49; Dec. 197
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  • 44
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    X-ray reflectometer for optical efficiency and scatter measurements (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An instrument has been developed to determine the reflection efficiency and scatter characteristics of optical samples at X-ray wavelengths from 1.5 to 113 A. The reflectometer operates in an oil-free vacuum chamber and measures the reflection efficiency and scatter characteristics as a function of the angle of incidence. The reflection efficiency is given for 8.34-A radiation incident on a fused silica sample finished to a flatness of one-tenth of a wavelength. The experimental reflection efficiency is compared with the theoretical data. The scatter curves are given for the direct X-ray beam and for the beam reflected from the fused silica sample at an angle of incidence of 50 arcmin. The full-width-at-half-maximum (FWHM) resolution of the instrument is approximately 13 arcsec, as determined by a least-squares smoothing of the experimental data.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 49; Dec. 197
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  • 45
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    An evaluation of electrochemical concentration cell sonde measurements of atmospheric ozone (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Using Dobson spectrophotometer measurements of total ozone as a comparison, an analysis of the Electrochemical Concentration Cell (ECC) ozonesonde's measurement accuracy is presented. Days of conjunctive ECC-Dobson observations (from 1970 to 1976 at Wallops Flight Center) provide a set of 123 pairs of total ozone values. Sample set statistics are generated with means and standard deviations of total ozone values and differences being noted. An in-depth study of factors such as time differences between associated observations, integration techniques used, assumptions used in calculating residual ozone and other possible sources of errors are examined. Short-period changes in total ozone using Dobson data during the observational period are also described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Applied Meteorology; 17; Oct. 197
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  • 46
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    Phase insensitive acoustoelectric transducer (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Conventional ultrasonic transducers transform acoustic waves into electrical signals preserving phase and amplitude information. When the acoustic wavelength is significantly smaller than the transducer diameter, severe phase modulation of the electrical signal can occur. This results in anomalous attenuation measurements, background noise in nondestructive evaluation, and in general complicates data interpretation. This article describes and evaluates a phase-insensitive transducer based on the acoustoelectric effect. Theory of operation of the acoustoelectric transducer (AET) is discussed, and some optimization procedures outlined for its use. Directivity data for the AET are contrasted with a conventional piezoelectric transducer. In addition, transmission scanning data of phantom flaws in metal plates are presented for both transducers and demonstrate a significant improvement in resolution with the AET.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Acoustical Society of America; vol. 64
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  • 47
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    Extending the field of view of KD/asterisk/P electrooptic modulators (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The use of KD(asterisk)P as a polarization rotator has been limited to small field of view instruments. To investigate this limitation, the index ellipsoid is used to describe the optical properties of KD(asterisk)P and to calculate the retardance and fast axis as a function of the angle of incidence and voltage. Computed converging light patterns are then compared with observed intensity patterns formed by KD(asterisk)P. Finally, computed intensity patterns are used to demonstrate how the field of view of KD(asterisk)P can be increased when properly aligned with a positive uniaxial crystal.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 17; Sept. 15
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  • 48
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    Balloon-borne photoionization mass spectrometer for measurement of stratospheric gases (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A balloon-borne photoionization mass spectrometer used to measure stratospheric trace gases is described. Ions are created with photons from high-intensity krypton discharge lamps and a quadrupole mass analyzer is employed for ion identification. Differential pumping is achieved with liquid helium cryopumping. To insure measurement of unperturbed stratospheric air, the entire system is contained in a sealed gondola and the atmospheric sample is taken some distance away during descent. The photoionization technique allows the detection of a low ionization potential constituent, such as nitric oxide, at less than a part in one billion in the presence of the major atmospheric gases and their isotopes. Operation of the mass spectrometer system was demonstrated during a daytime flight from Palestine, Texas on 26 April 1977. The sensitivity achieved and the unique selectivity afforded by this technique offer a capability for trace constituent measurement not possible with the more conventional electron impact ionization approach.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 49; Aug. 197
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  • 49
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    Narrow zone heating by a new radiation focusing technique - Toroidal ellipsoid furnace (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes the design of a toroidal ellipsoid furnace for narrow zone heating of materials in sealed transparent ampoules. The heater is a toroid flattened to an elliptical cross section like a partially inflated inner tube resting on a horizontal surface. The foci of the ellipsoid are two concentric rings. The outer focus is occupied by a heater wire, and the inner focus is arranged to fall on the surface of the cylindrical ingot within its transparent capsule. One advantage of the new furnace is that the wire heater closely approximates the ideal shape, lying along an extended line focus, as opposed to the elusive point source of the Costello furnace. Also, the ingot is heated uniformly around its circumference.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 49; Aug. 197
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  • 50
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    A method of determining spectral analytical dye densities (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A straightforward method for the user of color imagery to determine the spectral analytical density of dyes present in the processed imagery is presented. The method involves exposing a large number of different color patches on the film which span the gamut of the film's imaging capabilities. From integral spectral density measurements at 16 to 19 different wavelengths, the unit spectral dye curves for each of the three dyes present were determined in two different types of color films. A discussion of the use of these spectral dye densities to determine the transformation between integral density measurements and analytical density is presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Photogrammetric Engineering and Remote Sensing; 44; Oct. 197
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  • 51
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    Summary of system state-of-health measurements STRATCOM 8: A balloon experiment (1978)
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    Publication Date: 2011-08-17
    Description: Various measurements were made to determine the temperature and attitude of the gondola and the status of primary power and control equipment. Bead thermistors were used to measure temperatures at selected points throughout the gondola. A two-axis magnetometer and a two-axis pendulum were used to measure gondola attitude. Voltage and current measurements indicated the status of the primary power sources and associated power converters.
    Keywords: AERODYNAMICS
    Type: NASA. Goddard Space Flight Center STRATCOM 8 Data Workshop and Suppl.; p 24-31
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  • 52
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    Stratospheric composition balloon, aircraft and rocket-borne experiments, 28-30 September 1977 (systems, instruments, trajectories, supporting measurements) (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The STRATCOM (STRATospheric COMposition) is a long term multipurpose program for integrated, correlated measurements of stratospheric parameters related to composition, thermodynamics, and radiative balance. Balloon 8-b, carrying a solar-pointing grating infrared spectrometer, two CO2 thermal emission radiometers and two in-situ air temperature sensors was launched at 1251 MST on 28 September 1977 to float at an altitude of 39 km from 1521 MST with the instruments making measurements at that altitude through the time of sunset at 1822 MST. Balloon 8-a lifted a payload consisting of four UV filter photometers, two UV spectrometers, two chemiluminescent ozonesondes, dasibi ozone monitor, 14 tube cryogenic sampler, two aluminum oxide H2O sensors, four air temperature sensors, atmospheric pressure sensor, infrared and visible pyranometers, downward-looking camera, blunt-kryton lamp-Gerdien condenser probe, three component anemometer, balloon apex-plate payload and three parachute-borne dropsondes.
    Keywords: AERODYNAMICS
    Type: NASA. Goddard Space Flight Center STRATCOM 8 Data Workshop and Suppl.; p 10-23
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  • 53
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    A portable hypergolic oxidizer vapor sensor for NASA's Space Shuttle program (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design and performance characteristics of an electrochemical NO2 sensor selected by NASA for the space shuttle program is described. The instrument consists of a sample pump, an electrochemical cell, and control and display electronics. The pump pushes the sample through the electrochemical cell where the vapors are analyzed and an output proportional to the NO2 concentration is produced. The output is displayed on a panel meter, and is also available at a recorder jack. The electrochemical cell is made up of a polypropylene chamber covered with teflon membrane faceplates. Plantinum electrodes are bonded to the faceplates, and the sensing and counter electrodes are potentiostatically controlled at -200 mV with respect to the reference electrode. The cell is filled with electrolyte, consisting of 13.5 cc of 23% solution of KOH.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Proc. of the NASA(Fla. Inst. of Tech. Environ. Eng. Conf. on Nitrogen Tetroxide; p 1-10
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  • 54
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    In-flight Compressible Turbulent Boundary Layer Measurements on a Hollow Cylinder at a Mach Number of 3.0 (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Skin temperatures, shearing forces, surface static pressures, and boundary layer pitot pressures and total temperatures were measured on a hollow cylinder 3.04 meters long and 0.437 meter in diameter mounted beneath the fuselage of the YF-12A airplane. The data were obtained at a nominal free stream Mach number of 3.0 and at wall-to-recovery temperature ratios of 0.66 to 0.91. The free stream Reynolds number had a minimal value of 4.2 million per meter. Heat transfer coefficients and skin friction coefficients were derived from skin temperature time histories and shear force measurements, respectively. Boundary layer velocity profiles were derived from pitot pressure measurements, and a Reynolds analogy factor of 1.11 was obtained from the measured heat transfer and skin friction data. The skin friction coefficients predicted by the theory of van Driest were in excellent agreement with the measurements. Theoretical heat transfer coefficients, in the form of Stanton numbers calculated by using a modified Reynolds analogy between skin friction and heat transfer, were compared with measured values. The measured velocity profiles were compared to Coles' incompressible law-of-the-wall profile.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 259-286
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  • 55
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    Boundary layer, skin friction, and boattail pressure measurements from the YF-12 airplane at Mach numbers up to 3 (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In-flight measurements of boundary layer and skin friction data were made on YF-12 airplanes for Mach numbers between 2.0 and 3.0. Boattail pressures were also obtained for Mach numbers between 0.7 and 3.0 with Reynolds numbers up to four hundred million. Boundary layer data measured along the lower fuselage centerline indicate local displacement and momentum thicknesses can be much larger than predicted. Skin friction coefficients measured at two of five lower fuselage stations were significantly less than predicted by flat plate theory. The presence of large differences between measured boattail pressure drag and values calculated by a potential flow solution indicates the presence of vortex effects on the upper boattail surface. At both subsonic and supersonic speeds, pressure drag on the longer of two boattail configurations was equal to or less than the pressure drag on the shorter configuration. At subsonic and transonic speeds, the difference in the drag coefficient was on the order of 0.0008 to 0.0010. In the supersonic cruise range, the difference in the drag coefficient was on the order of 0.002. Boattail drag coefficients are based on wing reference area.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 227-258
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  • 56
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    Flight-measured pressure characteristics of aft-facing steps in thick boundary layer flow for transonic and supersonic Mach numbers (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Aft-facing step base pressure flight data were obtained for three step heights for nominal transonic Mach numbers of 0.80, 0.90, and 0.95, and for supersonic Mach numbers of 2.2, 2.5, and 2.8 with a Reynolds number, based on the fuselage length ahead of the step, of about 10 to the 8th power. Surface static pressures were measured ahead of the step, behind the step, and on the step face (base), and a boundary layer rake was used to obtain boundary layer reference conditions. A comparison of the data from the present and previous experiments shows the same trend of increasing base pressure ratio (decreasing drag) with increasing values of momentum thickness to step height ratios. However, the absolute level of these data does not always agree at the supersonic Mach numbers. For momentum thickness to height ratios near 1.0, the differences in the base pressure ratios appear to be primarily a function of Reynolds number based on the momentum thickness. Thus, for Mach numbers above 2, the data analyzed show that the base pressure ratio decreases (drag increases) as Reynolds number based on momentum thickness increases for a given momentum thickness and step height.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 201-226
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  • 57
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    Wind tunnel evaluation of YF-12 inlet response to internal airflow disturbances with and without control (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The response of terminal-shock position and static pressures in the subsonic duct of a YF-12 aircraft flight-hardware inlet to perturbations in simulated engine corrected airflow were obtained with and without inlet control. Frequency response data, obtained with inlet controls inactive, indicated the general nature of the inherent inlet dynamics, assisted in the design of controls, and provided a baseline reference for responses with active controls. All the control laws were implemented by means of a digital computer that could be programmed to behave like the flight inlet's existing analog control. The experimental controls were designed using an analytical optimization technique. The capabilities of the controls were limited primarily by the actuation hardware. The experimental controls provided somewhat better attenuation of terminal shock excursions than did the YF-13 inlet control. Controls using both the forward and aft bypass systems also provided somewhat better attenuation than those using just the forward bypass. The main advantage of using both bypasses is in the greater control flexibility that is achieved.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Res. Center YF-12 Experiments Symp., Vol. 1; p 157-192
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  • 58
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    Pilot Workload Measurement and Experience on Supersonic Cruise Aircraft (1978)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Aircraft parameters and physiological parameters most indicative of crew workload were investigated. Recommendations were used to form the basis for a continuing study in which variations of the interval between heart beats are used as a measure of nonphysical workload. Preliminary results are presented and current efforts in further defining this physiological measure are outlined.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 121-134
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  • 59
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    The YF-12 Gust Velocity Measuring System (1978)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A true gust velocity measuring system designed to alleviate complications resulting from airframe flexibility and from the high-speed, high-temperature environment of supersonic cruise aircraft was evaluated on a YF-12 airplane. The system uses fixed vanes on which airflow direction changes produce differential pressure variations that are measured. Airframe motions, obtained by postflight integration of recorded angular rate and linear acceleration data, are removed from the flow angle data. An example of turbulence data obtained at high-altitude, supersonic flight conditions is presented and compared with previous high-altitude turbulence measurements obtained with subsonic aircraft and with turbulence criteria contained in both military and civil design specifications for supersonic cruise vehicles. Results of these comparisons indicate that the YF-12 turbulence sample is representative of turbulence present in the supersonic cruise environment.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 135-154
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  • 60
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    Flight experience with altitude hold and Mach hold autopilots on the YF-12 aircraft at Mach 3 (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The altitude hold mode of the YF-12A airplane was modified to include a high-pass-filtered pitch rate feedback along with optimized inner loop altitude rate proportional and integral gains. An autothrottle control system was also developed to control either Mach number or KEAS at the high-speed flight conditions. Flight tests indicate that, with the modified system, significant improvements are obtained in both altitude and speed control, and the combination of altitude and autothrottle hold modes provides the most stable aircraft platform thus far demonstrated at Mach 3 conditions.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 97-119
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  • 61
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    Flight-Measured Aerodynamic Loads on a 0.92 Aspect Ratio Lifting Surface (1978)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Ventral fin loads, expressed as normal force coefficients, bending moment coefficients, and torque coefficients, were measured during flight tests of a YF-12A airplane. Because of the proximity of the ventral fin to the ailerons, the aerodynamic loads presented were the result of both sideslip loads and aileron crossflow loads. Aerodynamic data obtained from strain gage loads instrumentation and some flight pressure measurements are presented for several Mach numbers ranging from 0.70 to 2.00. Selected wind tunnel data and results of linear theoretical aerodynamic calculations are presented for comparison.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 73-91
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  • 62
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    Overview of the NASA YF-12 program (1978)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The history of NASA's interest in supersonic research and the agency's contribution to the development of the YF 12 aircraft is reviewed as well as the program designed to use that aircraft as a test bed for supersonic cruise research. Topics cover elements of the program, project organization, and major accomplishments.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 3-25
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    Recent Load Calibrations Experience with the YF-12 Airplane (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of calibrated strain gages to measure wing loads on the YF-12A airplane is discussed as well as structural configurations relative to the thermal environment and resulting thermal stresses. A thermal calibration of the YF-12A is described to illustrate how contaminating thermal effects can be removed from loads equations. The relationship between ground load calibrations and flight measurements is examined for possible errors, and an analytical approach to accommodate such errors is presented.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 47-72
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  • 64
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    Wake vortex technology (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A brief overview of the highlights of NASA's wake vortex minimization program is presented. The significant results of this program are summarized as follows: (1) it is technically feasible to reduce significantly the rolling upset created on a trailing aircraft; (2) the basic principles or methods by which reduction in the vortex strength can be achieved have been identified; and (3) an analytical capability for investigating aircraft vortex wakes has been developed.
    Keywords: AERODYNAMICS
    Type: CTOL Transport Technol., 1978; p 757-771
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  • 65
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    Development of advanced stability theory suction prediction techniques for laminar flow control (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The problem of obtaining accurate estimates of suction requirements on swept laminar flow control wings was discussed. A fast accurate computer code developed to predict suction requirements by integrating disturbance amplification rates was described. Assumptions and approximations used in the present computer code are examined in light of flow conditions on the swept wing which may limit their validity.
    Keywords: AERODYNAMICS
    Type: CTOL Transport Technol. 1978; p 375-394
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  • 66
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    Laminar flow control overview (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Application of laminar flow control technology to future CTOL long range transport aircraft was considered. Topics covered include: (1) airfoil development and test; (2) development and improvement of design methods; (3) evaluation of leading edge contamination; and (4) laminar flow control system definition and concept evaluation.
    Keywords: AERODYNAMICS
    Type: CTOL Transport Technol., 1978; p 349-356
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  • 67
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    X-ray source characteristics and detection efficiencies of prototype Lixiscopes (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The radioactive X-ray sources and scintillator screens used in prototype Lixiscope units are described. Some of those considerations necessary for the optimization of future Lixiscope designs are stressed as well as some semi-quantitative information on the present prototype devices.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 11-14
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  • 68
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    Orthopedic evaluation (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The clinical performance of the Lixiscope in orthopedics was compared with routine radiography. Portability and size were the major advantages of the Lixiscope. The main disadvantage at this point in time was the Lixiscope's inability to study large areas.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 31-35
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  • 69
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    Some contemplated improvements to the prototype Lixiscope (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some contemplated improvements on the Lixiscope are described. These can be divided roughly into two categories: those which are well within existing technology, and thus can be implemented immediately; and those which are more at the state-of-the-art level, and which are directly related to applications in X-ray and gamma ray imaging in astronomy.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Preliminary Appl. and Evaluation Results. Lixiscope; p 15-18
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  • 70
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    Dental research: Preliminary observations and projections (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The potential applicability of the Lixiscope in dentistry was investigated. Conceptual limitations on basic design requirements common to the Lixiscope are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 37-41
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  • 71
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    Podiatry (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of the Lixiscope in podiatry was preliminarily evaluated. It is concluded that the possibilities for the Lixiscope's clinical use in podiatry seems endless.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 61-64
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  • 72
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    Maxillo: Facial diagnosis (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of the Lixiscope in dentistry was studied. Due to a problem in resolution, it is concluded that, at this present time, the Lixiscope can only be as a previewing device for conventional radiography.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 45-49
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  • 73
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    Theoretical calculations and instrument development and test characterization of low intensity X-ray imaging devices (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The characteristics of the Lixiscope when excited by X-rays produced by conventional electrically powered X-ray generators are explored to determine the optimum X-ray spectrum and mode of operation of the generator, which yields satisfactory Lixiscope images of medical and industrial specimens.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 7-10
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  • 74
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    Pediatrics (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The utilization of the Lixiscope in pediatrics was investigated. The types of images that can presently be obtained are discussed along with the problems encountered. Speculative applications for the Lixiscope are also presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 51-59
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  • 75
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    Future progress in the development of the Lixiscope (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some of the potential of the lixiscope in astrophysics as well as in space medicine are reported. The positioning of the lixiscope as a sensitive detector placed at the focal plane of a focusing or collimating X-ray telescope, and studies of the inter-coastal spacing during weightlessness are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Preliminary Appl. and Evaluation Results. Lixiscope 5-6 (SEE N80-12384 03-35)
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  • 76
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    Dosimetric considerations in dental applications (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The integration of the Lixiscope into dental procedures was studied and compared with conventional dental radiographic techniques. It was found that through the use of intraoral sealed sources in conjunction with microchannel plate technology, the Lixiscope gives increased diagnostic information with decreased radiation dosage.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 43-44
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  • 77
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    A comparison of the Lixiscope with other X-ray imaging systems (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The imaging techniques relevant in the determination of the clinical potential of the Lixiscope are reviewed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 19-27
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  • 78
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    The Lixiscope concept (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A portable X-ray imagery instrument which utilizes a converter phosphor or scintillator to convert the X-ray image into visible light image is described. The potential medical as well as industrial applications of the Lixiscope are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Preliminary Appl. and Evaluation Results. Lixiscope; p 3-4
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  • 79
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    An analysis of prop-fan/airframe aerodynamic integration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An approach to aerodynamic integration of turboprops and airframes, with emphasis placed upon wing mounted installations is addressed. Potential flow analytical techniques were employed to study aerodynamic integration of the prop fan propulsion concept with advanced, subsonic, commercial transport airframes. Three basic configurations were defined and analyzed: wing mounted prop fan at a cruise Mach number of 0.8, wing mounted prop fan in a low speed configuration, and aft mounted prop fan at a cruise Mach number of 0.8.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152186 , NAS 1.26:152186 , D6-47113
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  • 80
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    A correlation method to predict the surface pressure distribution on an infinite plate from which a jet is issuing (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A correlation method to predict pressures induced on an infinite plate by a jet issuing from the plate into a subsonic free stream was developed. The complete method consists of an analytical method which models the blockage and entrainment properties of the jet and a correlation which accounts for the effects of separation. The method was developed for jet velocity ratios up to ten and for radial distances up to five diameters from the jet. Correlation curves and data comparisons are presented for jets issuing normally from a flat plate with velocity ratios one to twelve. Also, a list of references which deal with jets in a crossflow is presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152160 , NEAR-TR-160
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  • 81
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    Pressure Distributions for the GA(W)-2 Airfoil with 20% Aileron, 25% Slotted Flap and 30% Fowler Flap (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Surface pressure distributions were measured for the 13% thick GA(W)-2 airfoil section fitted with 20% aileron, 25% slotted flap and 30% Fowler flap. All tests were conducted at a Reynolds number of 2.2 x 10 to the 6th power and a Mach number of 0.13. Pressure distribution and force and moment coefficient measurements are compared with theoretical results for a number of cases. Agreement between theory and experiment is generally good for low angles of attack and small flap deflections. For high angles and large flap deflections where regions of separation are present, the theory is inadequate. Theoretical drag predictions are poor for all flap-extended cases.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2948 , AR-76-3
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  • 82
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    A computer program to calculate the longitudinal aerodynamic characteristics of upper-surface-blown wing-flap configurations (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A user's manual is presented for a computer program in which a vortex-lattice lifting-surface method is used to model the wing and multiple flaps. The engine wake model consists of a series of closely spaced vortex rings with rectangular cross sections. The jet wake is positioned such that the lower boundary of the jet is tangent to the wing and flap upper surfaces. The two potential flow models are used to calculate the wing-flap loading distribution including the influence of the wakes from up to two engines on the semispan. The method is limited to the condition where the flow and geometry of the configurations are symmetric about the vertical plane containing the wing root chord. The results include total configuration forces and moments, individual lifting-surface load distributions, pressure distributions, flap hinge moments, and flow field calculation at arbitrary field points. The use of the program, preparation of input, the output, program listing, and sample cases are described.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3005 , NEAR-TR-158
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  • 83
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    Preliminary design of the cryogenic cooled limb scanning interferometer radiometer (CLIR) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The preliminary design of the cryogenic cooling system for the Cryogenic Cooled Limb Scanning Interferometer Radiometer (CLIR) instrument to be flown on the Atmospheric Magnetospheric Physics Satellite (AMPS) was studied. The top level trade studies were extensive due to the instrument requirement for cooling at three temperature levels as opposed to the two levels initially described for the instrument. Approximately 12 different combinations of cryogens were investigated. The basic lifetime requirement for the instrument was 30 days. However, studies were also conducted for a follow-up mission requiring a 1 year lifetime. The top level trades led to the selection of a single stage supercritical helium baseline.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-166684 , LMSC-D626264
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  • 84
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    Static tests of the J97 powered, external augmenter V/STOL wind tunnel model (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of the static testing (zero forward speed) of the J97-powered, external augmentor, large scale, V/STOL model are discussed. With a ground clearance of 7.5 feet, believed to have put the model essentially out of ground effect, a gross thrust augmentation ratio of 1.60 at nozzle pressure ratio (NPR) = 3.0 was measured for the fuselage augmentor. A similar figure was apparent for the wing augmentor. An overall ratio of model thrust to bare engine thrust of 1.52 was determined at NPR = 3.0. The structural integrity of the model was well demonstrated and duct pressure losses were small.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152403 , DHC-DND-77-4
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  • 85
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    Steady state spurious errors in shock-capturing numerical schemes (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The behavior of the steady state spurious error modes of the MacCormack scheme and the upwind scheme of Warming and Beam was obtained from a linearized difference equation for the steady state error. It was shown that the spurious errors can exist either as an eigensolution of the homogeneous part of this difference equation or because of excitation from large discretization errors near oblique shocks. It was found that the upwind scheme does not permit spurious oscillations on the upstream side of shocks. Examples are given for the inviscid Burgers' equation and for one and two dimensional gasdynamic flows.
    Keywords: AERODYNAMICS
    Type: KTH-AERO-TN-60 , TRITA-FPT-032
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  • 86
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    The aerodynamic design of an advanced rotor airfoil (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An advanced rotor airfoil, designed utilizing supercritical airfoil technology and advanced design and analysis methodology is described. The airfoil was designed subject to stringent aerodynamic design criteria for improving the performance over the entire rotor operating regime. The design criteria are discussed. The design was accomplished using a physical plane, viscous, transonic inverse design procedure, and a constrained function minimization technique for optimizing the airfoil leading edge shape. The aerodynamic performance objectives of the airfoil are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2961 , LG77ER0208
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  • 87
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    Interaction of a two-dimensional strip boundary layer with a three-dimensional transonic swept-wing code (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 3D inviscid transonic analysis code was combined with a 2D strip integral boundary layer technique to form an approximate interaction procedure for analyzing the flow over a high aspect ratio wing near cruise conditions. Converged results obtained using the procedure for an aspect ratio 10.3 supercritical wing are discussed. Angle of attack adjustments were made during the iterative procedure in order to compensate for the viscous lift loss. A comparison of the calculations with experimental data is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78640
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  • 88
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    Cloud Top Scanning radiometer (CTS) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A scanning radiometer to be used for measuring cloud radiances in each of three spectral regions is described. Significant features incorporated in the Cloud Top Scanner design are: (1) flexibility and growth potential through use of easily replaceable modular detectors and filters; (2) full aperture, multilevel inflight calibration; (3) inherent channel registration through employment of a single shared field stop; and (4) radiometric sensitivity margin in a compact optical design through use of Honeywell developed (Hg,Cd)Te detectors and preamplifiers.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-159954 , HONEYWELL-7804-5
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  • 89
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    Towards complete configurations using an embedded grid approach (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new approach to simulating transonic flow about transport configurations is briefly outlined. The methods embedded grid scheme provides a high degree of computational resolution coupled with geometric flexibility for future applications to complex shapes. Calculations presented illustrate aspects of transonic transport design including fuselage design, determination of wing control surface deflection effectiveness, and wing design.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3030
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  • 90
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    Preliminary design of the cryogenic cooled limb scanning interferometer radiometer (CLIR), phase 2 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A cryogenic system to be utilized with a mounted pointing system is designed. The analysis indicates that the resulting design is significantly heavier than previous design due to the increased diameter of the system, resulting in greater tank and vacuum enclosure weights. Additional weight is also required in the area where the payload is attached to the pointing system in order to provide additional stiffness to the payload. The vacuum shell required to enclose the instrument is shorter and therefore an attendant reduction in instrument package weight would be expected. The primary resonance of the cooler instrument package occurs at 21 Hz, a mode in which the flexibility of the vacuum shell allows motion of the cryogen tank and instrument, and which can be increased by additional stiffening in the region of the pointing system vacuum shell connection at the cost of additional weight. The second resonance at 59 Hz is due to vibration of the helium tank on the fiberglass support tubes. The parasitic heat load can be reduced to 0.28 W by the utilization of a sandwich support tube structure in place of the monocoque structure assumed in the design.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-159992 , LMSC-D633472
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  • 91
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    A computer program for calculating aerodynamic characteristics of low aspect-ratio wings with partial leading-edge separation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The necessary information for using a computer program to predict distributed and total aerodynamic characteristics for low aspect ratio wings with partial leading-edge separation is presented. The flow is assumed to be steady and inviscid. The wing boundary condition is formulated by the Quasi-Vortex-Lattice method. The leading edge separated vortices are represented by discrete free vortex elements which are aligned with the local velocity vector at midpoints to satisfy the force free condition. The wake behind the trailing edge is also force free. The flow tangency boundary condition is satisfied on the wing, including the leading and trailing edges. The program is restricted to delta wings with zero thickness and no camber. It is written in FORTRAN language and runs on CDC 6600 computer.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145362 , CRINC-FRL-266-2
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  • 92
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    Design and analytical study of a rotor airfoil (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airfoil section for use on helicopter rotor blades was defined and analyzed by means of potential flow/boundary layer interaction and viscous transonic flow methods to meet as closely as possible a set of advanced airfoil design objectives. The design efforts showed that the first priority objectives, including selected low speed pitching moment, maximum lift and drag divergence requirements can be met, though marginally. The maximum lift requirement at M = 0.5 and most of the profile drag objectives cannot be met without some compromise of at least one of the higher order priorities.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2988 , D210-11239-1
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  • 93
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    Aerodynamic preliminary analysis system. Part 1: Theory (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A comprehensive aerodynamic analysis program based on linearized potential theory is described. The solution treats thickness and attitude problems at subsonic and supersonic speeds. Three dimensional configurations with or without jet flaps having multiple non-planar surfaces of arbitrary planform and open or closed slender bodies of non-circular contour may be analyzed. Longitudinal and lateral-directional static and rotary derivative solutions may be generated. The analysis was implemented on a time sharing system in conjunction with an input tablet digitizer and an interactive graphics input/output display and editing terminal to maximize its responsiveness to the preliminary analysis problem. Nominal case computation time of 45 CPU seconds on the CDC 175 for a 200 panel simulation indicates the program provides an efficient analysis for systematically performing various aerodynamic configuration tradeoff and evaluation studies.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145284
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  • 94
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    A computational model for the prediction of jet entrainment in the vicinity of nozzle boattails (The BOAT code) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The basic code structure is discussed, including the overall program flow and a brief description of all subroutines. Instructions on the preparation of input data, definitions of key FORTRAN variables, sample input and output, and a complete listing of the code are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159001
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  • 95
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    Flap survey test of a combined surface blowing model: Flow measurements at static flow conditions (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Combined Surface Blowing (CSB) V/STOL lift/propulsion system consists of a blown flap system which deflects the exhaust from a turbojet engine over a system of flaps deployed at the trailing edge of the wing. Flow measurements consisting of velocity measurements using split film probes and total measure surveys using a miniature Kiel probe were made at control stations along the flap systems at two spanwise stations, the centerline of the nozzle and 60 percent of the nozzle span outboard of the centerline. Surface pressure measurements were made in the wing cove and the upper surface of the first flap element. The test showed a significant flow separation in the wing cove. The extent of the separation is so large that the flow into the first flap takes place only at the leading edge of the flap. The velocity profile measurements indicate that large spanwise (3 dimensional) flow may exist.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152124
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  • 96
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    Measurements of pulse-height defect in Au-Si detectors for H, He, C, N, O, Ne, Ar, Kr from about 2 to 400 keV/nucleon (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: We report measurements of pulse-height defects in Si surface-barrier detectors for a variety of ions and energies. We find: (1) for ions up to Ne our measurements agree remarkably well with calculations based on energy loss and nuclear defect theory, (2) for heavier ions we find systematic deviations, (3) there is no evidence of a dead layer at the Si-Au interface, and (4) our measurements are consistently reproducible for detectors fabricated in our laboratory.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 154,; 1978
    Format: text
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  • 97
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    The Palermo four-color far infrared program (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A four-channel far-IR photometer designed for use with a balloon-borne 102-cm telescope is described. The data analysis system for this photometer is discussed, and a typical observational program is outlined. Possible objects that may be observed with the four-color far-IR photometer include molecular clouds, the galactic-center region, H II regions, quasars, Seyfert galaxies, and BL Lacertae objects.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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  • 98
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    Theory of crossed-beam diffraction gratings (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The operation of crossed-beam gratings is analyzed in terms of diffraction efficiency and beam quality, following Solymar's method's. General solutions for arbitrary beam widths, general beam profiles, and illumination with two beams are derived. A scheme for improving the beam quality of these gratings is proposed. The analysis should be useful in integrated optics for designing beam expanders, beam contractors, and mirrors, and for analyzing waveguide interferometers.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Journal of Quantum Electronics; QE-14; Dec. 197
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  • 99
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    Numerical solution of the Navier-Stokes equations for arbitrary blunt bodies in supersonic flows (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A time-dependent, two-dimensional Navier-Stokes code employing the body-fitted coordinate technique has been developed for supersonic flows past blunt bodies of arbitrary shape. The computer program is based on the finite-difference approximation of the compressible Navier-Stokes equations transformed to nonorthogonal curvilinear coordinates with the contravariant components of the velocity vector as dependent variables. The bow shock ahead of the body is obtained as part of the solution, by 'shock capturing'. Numerical solutions of the complete equations are presented in detail for free-stream Mach number 4.6, Reynolds number 10,000, and an isothermal wall temperature of 556 K for a circular cylinder with the free-stream outer boundaries forming a hyperbola in the front and a circular arc in the back.
    Keywords: AERODYNAMICS
    Type: Numerical Heat Transfer; 1; Oct
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  • 100
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    Improved detectivity of pyroelectric detectors (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: High detectivity single-element SBN pyroelectric detectors were fabricated. The theory and technology developments related to improved detector performance were identified and formulated. Improved methods of material characterization, thinning, mounting, blackening and amplifier matching are discussed. Detectors with detectivities of 1.3 x 10 to the 9th power square root of Hz/watt at 1 Hz are reported. Factors limiting performance and recommendations for future work are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-158917
    Format: application/pdf
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