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  • SPACE SCIENCES  (1.758)
  • Chemical Engineering  (983)
  • AERODYNAMICS  (669)
  • SPACE VEHICLES  (609)
  • Cell & Developmental Biology  (608)
  • SPACE RADIATION  (592)
  • 1975-1979  (1.217)
  • 1970-1974  (3.581)
  • 1960-1964  (421)
  • 1978  (1.217)
  • 1972  (3.581)
  • 1961  (421)
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  • 1975-1979  (1.217)
  • 1970-1974  (3.581)
  • 1960-1964  (421)
Jahr
  • 1
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    A parametric experimental study of the slotted-wall boundary condition (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 459-471
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  • 2
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    A procedure for analyzing transonic flow over harmonically oscillating airfoils (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 657-670
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  • 3
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    Section drag coefficients from pressure probe transverses of a wing wake at low speeds (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 601-621
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  • 4
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    Some calculations of transonic potential flow for the NACA 64A006 airfoil with oscillating flap (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 689-700
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  • 5
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    Applications of dynamic measurement techniques to wind-tunnel testing (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 571-588
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  • 6
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    Interpretation of observed cosmic microwave background radiation (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-17
    Beschreibung: The Alfven and Mendis (1977) conclusion that dust grains in galaxies render the universe opaque to cosmic microwave background at a red shift ratio equal to 40 is challenged by a calculation of the opacity of galactic dust grains to the microwave background radiation from the time of decoupling at emission red shift ratio equal to 1500 to the present in the standard big bang model. In the present calculation, evolutionary effects on grain opacity and abundance are estimated. At wavelengths used in studying the microwave background, the optical depth of the grains is found to be 0.18 when the deceleration parameter equals 0.03, and 0.05 when the deceleration parameter equals 0.5. The results indicate that microwave background can provide information on an early dense phase of the universe.
    Schlagwort(e): SPACE RADIATION
    Materialart: Nature; 271; Feb. 2
    Format: text
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  • 7
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    Background of a shielded Ge(Li) spectrometer at balloon altitudes (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-17
    Beschreibung: The background data obtained from an actively shielded Ge(Li) spectrometer flown on a balloon were analyzed and a preliminary model was developed to explain background features including the intensity and time profile of line emission. These features can be explained by a combination of secondary radiation originating in the CsI shield and atmospheric secondary radiation leaking through it.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 462-472
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  • 8
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    Gamma-ray line emission above 8 MeV (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-17
    Beschreibung: The spectra of energetic nuclei within astrophysical sources may be determined by studying gamma-ray line emissions above 8 MeV. Excited states which can be produced by inelastic scattering, charge exchange, and spallation reactions in the abundant nuclear species were considered in order to identify nuclear lines which may contribute to the gamma spectrum. The cross sections for production of most high-energy states are sparsely measured. Those which were determined are comparable to the cross section for production of the 15.11 MeV level in C-12 with few exceptions. The branching ratios for gamma-ray and particle emission are, however, better known. Of those states considered, 44 measured branching ratios greater than 40% for emission of a gamma-ray with energy above 8 MeV. For twelve more states the branching ratios, although not yet determined, are expected to be small. The gamma-ray emission from other individual nuclear states is not likely to be as great as that that for the 15.11 MeV state in C-12.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 323-329
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  • 9
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    Galactic center iron line emission (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Data from the Goddard Space Flight Center experiment on HEAO 1 were examined for galactic center iron line emission. Evidence for a 6.8 keV line from the summed flux within 10 deg longitude and 10 deg latitude of the galactic center was found; however, firm limits cannot be put on the intrinsic line width. If the line emission is diffuse and cosmic-ray-induced, the calculations of Bussard et al (1978) yield an upper limit to c-12 4.44 MeV line emission, which is not inconsistent with the results of Haymes et al (1975). Significant contributions to the iron line from discrete sources can not be ruled out.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 302-309
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  • 10
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    Planetary gamma-ray spectroscopy (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The measured intensities of certain gamma rays of specific energies escaping from a planetary surface can be used to determine the abundances of a number of elements. The fluxes of the more intense gamma-ray lines emitted from 32 elements were calculated using current nuclear data and existing models for the source processes. The source strengths for neutron-capture reactions were modified from those previously used. The fluxes emitted form a surface of average lunar composition are reported for 292 gamma-ray lines. These theoretical fluxes were used elsewhere to convert the data from the Apollo gamma-ray spectrometers to elemental abundances and can be used with measurements from future missions to map the concentrations of a number of elements over a planet's surface. Detection sensitivities for these elements are examined and applications of gamma-ray spectroscopy for future orbiters to Mars and other solar-system objects are discussed.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 98-148
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  • 11
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    Aerodynamic effects (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-18
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: UAH(NASA Workshop on the Use of a Tethered Satellite System; p 151-155
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  • 12
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    Prospects for computational aerodynamics (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 221-227
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  • 13
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    Modeling of the Reynolds stresses (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Future Computer Requirements for Computational Aerodynamics; p 239-247
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  • 14
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    Computational aerodynamics and the numerical aerodynamic simulation facility (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Future Computer Requirements for Computational Aerodynamics; p 5-30
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  • 15
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    Carbon vaporization into a nonequilibrium, stagnation-point boundary layer (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 16; July 197
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  • 16
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    Perturbations in two- and three-dimensional transonic flows (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 16; July 197
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  • 17
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    Diffuse gamma radiation (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Results are reported for an investigation of the intensity, energy spectrum, and spatial distribution of the diffuse gamma radiation detected by SAS 2 away from the galactic plane in the energy range above 35 MeV. The gamma-ray data are compared with relevant data obtained at other wavelengths, including 21-cm emission, radio continuum radiation, and the limited UV and radio information on local molecular hydrogen. It is found that there are two quite distinct components to the diffuse radiation, one of which shows a good correlation with the galactic matter distribution and continuum radiation, while the other has a much steeper energy spectrum and appears to be isotropic at least on a coarse scale. The galactic component is interpreted in terms of its implications for both local and more distant regions of the Galaxy. The apparently isotropic radiation is discussed partly with regard to the constraints placed on possible models by the steep energy spectrum, the observed intensity, and an upper limit on the anisotropy.
    Schlagwort(e): SPACE RADIATION
    Materialart: Astrophysical Journal; vol. 222
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  • 18
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    High resolution spectroscopy from low altitude satellites (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The P 78 1 satellite to be placed in a synchronous polar orbit at an altitude of 550-660 km will carry two identical high resolution spectrometers each consisting of a single (approximately 85 cc) intrinsic germanium IGE detector. The payload also includes a pair of phoswitch scintillators, an array of CdTe detectors and several particle detectors, all of which are mounted on the wheel of the satellite. The intrinsic high purity IGE detectors receive cooling from two Stirling cycle refrigerators and facilitate the assembly of large and complex detector arrays planned for the next generation of high sensitivity instruments such as those planned for the gamma ray observatory. The major subsystems of the spectrometer are discussed as well as its capabilities.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 529-540
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  • 19
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    Theory of the accretion column and cyclotron radiation in X ray pulsars (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The energetics of the decelerating matter in the accretion column of X-ray pulsars is considered, in particular the Coulomb process. A two zone model is presented to account for the continuum and cyclotron line emission, incorporating a fan-beam radiation scheme, which appears able to explain the observed properties.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 425-433
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  • 20
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    Cyclotron emission in neutron star magnetospheres (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Kinematic aspects of cyclotron emission in superstrong magnetic fields are reviewed to suggest characteristic features which might be useful in confirming the nature of the reported line feature near 50 keV in the spectrum of Her X-1. The role of the inverse process of cyclotron absorption is also discussed.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 394-403
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  • 21
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    Measurements of 15.11-MeV gamma-ray flux produced in the reactions C-12(p, p')-C-12*(15.11 MeV) and O-16(p, p' alpha)-C-12*(15.11 MeV) (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-17
    Beschreibung: The flux of 15.11 MeV gamma rays relative to the flux of 4.44 MeV gamma rays which are emitted from the corresponding states of C-12 are a sensitive measure of the spectrum of exciting particles in solar flares and other cosmic sources. Emission of 15.11 MeV gamma rays may result not only from the direct excitation of C-12 but also from the interaction O-16 (p,p' alpha) C-12* sup 15.11 MeV. Although the cross sections for the direct reaction was studied extensively, the cross section for the spallation interaction with O-16 is not reported in the literature. Preliminary measurements demonstrated the feasibility of measuring the production of 15.11 MeV gamma rays by proton interactions with O-16 using the University of Maryland cyclotron facility. For both carbon and oxygen targets the flux of 15.11 MeV gamma rays is being measured relative to the flux of 4.44 MeV gamma rays. The gamma ray emission from de-excitation of the giant dipole resonances is being measured.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 502-511
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  • 22
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    Confidence about line features in Her X-1 spectrum (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: A balloon borne X-ray telescope was flown Aire-surl'Adour, France to search for pulsation of the X-ray source HER X1. The source was measured for about 3500 s relative exposure larger than 0.75 and features were detected at 57.5 plus or minus 7.5 keV and 135 plus or minus 10 keV in the spectrum. Data were reanalyzed in terms of possibility of gain shift encoder. The very strong dependence of the line features on such a shift is discussed.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 346-370
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  • 23
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    Gamma-ray lines from neutron stars as probes of fundamental physics (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The detection of gamma-ray lines produced at the surface of neutron stars will serve to test both the strong and gravitational interactions under conditions unavailable in terrestrial laboratories. Observation of a single redshifted gamma-ray line, combined with an estimate of the mass of the star will serve as a strong constraint on allowable equations of state of matter at supernuclear densities. Detection of two redshifted lines arising from different physical processes at the neutron star surface can provide a test of the strong principle of equivalence. Expected fluxes of nuclear gamma-ray lines from accreting neutron stars were calculated, including threshold, radiative transfer and redshift effects. The most promising probes of neutron star structure are the deuterium formation line and the positron annihilation line. Detection of sharp redshifted gamma-ray lines from X-ray sources such as Cyg X-1 would argue strongly in favor of a neutron star rather than black hole identification for the object.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 275-282
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  • 24
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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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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
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  • 25
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    Unsteady vortical and entropic distortions of potential flows round arbitrary obstacles (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Fluid Mechanics; 89; Dec. 13
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  • 26
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    Reynolds number influence on leeside flowfields (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 16; Dec. 197
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  • 27
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    Unsteady flow in a supersonic cascade with subsonic leading-edge locus (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 16; Dec. 197
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  • 28
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    Relative abundance of antiprotons and antihelium in the primary cosmic radiation (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The paper reports measurement of the antiproton-to-proton and antihelium-to-helium ratios in the 4-100 GeV/c range. A superconducting magnet spectrophotometer obtained the data during a balloon flight in May 1976. The upper limit value for the antiproton ratio is 0.0005 in the 4.2-12.5 GeV/c range. This value is only slightly higher than the expected value for a leaky box-model and nearly equal to the value expected in the Peter-Westergard model. It is suggested that this upper limit value rules out the closed galaxy model. Upper limit values for the antihelium ratio are 0.000058 in the 4-10 GeV/c range; less than 0.0001 in the 4-33 GeV/c range; and less than 0.01 in the 33-100 GeV/c range. The interpretation of the raw data is explained.
    Schlagwort(e): SPACE RADIATION
    Materialart: Nature; 274; July 13
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  • 29
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    Inlet boundary-layer shapes on four aircraft forebodies at Mach 6 (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft; 15; Jan. 197
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  • 30
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    The ISEE-C gamma ray burst spectrometer (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The technical properties, operation, and expected sensitivity are discussed for an experiment intended to search for narrow lines in the spectra of gamma ray bursts during the ISEE-C mission. At the heart of the experiment is a radiatively cooled germanium solid state photon detector. The instrumentation is capable of storing the entire spectrum of all but the largest bursts in the energy range 0.05-6.5 MeV. In addition, it analyzes the signals from two CsI detectors in two other experiments on the spacecraft and records event time histories from these to a few millisecond accuracy. A background mode permits spectral analysis during quiet times and will allow the determination of physically interesting upper limits for narrow lines in the diffuse gamma ray background radiation.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 516-528
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  • 31
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    The excitation of electronic transverse energy levels in an intense magnetic field (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Observations of the X-ray pulsar Hercules X-1 show a line emission feature at about 60 keV, which has been interpreted as the fundamental electron cyclotron line in a magnetic field of around six trillion gauss. In this interpretation, the line radiation results from transitions between transverse energy levels, which are quantized by the field. The expected line luminosity from the excitation of these levels by protons which are falling into the polar cap of a neutron star are calculated. They are assumed to attain kinetic energies up to around 200 MeV, the gravitational potential energy at the surface. The cross sections for high energy Coulomb encounters between small pitch angle protons and electrons in a strong field are measured and used to calculate the energy loss rate of the infalling protons. This rate, together with the rate of elastic nuclear proton collisions, is then used to calculate the number of line photons an infalling proton can be expected to produce, directly or indirectly. The results are applied to Hercules X-1.
    Schlagwort(e): SPACE RADIATION
    Materialart: ma Ray Spectry. In Astrophys.; p 404-417
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  • 32
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    Cyclotron lines from Her X-1 (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Data obtained during four balloon flight observations of hard X-ray emission from Her X-1 provide strong support for the existence of a spectral line feature at 54 keV to 58 keV, while the existence of a second harmonic is uncomfirmed. Because it is difficult to explain the observed feature by a second continuum spectrum or by atomic or nuclear processes, an interpretation in terms of a cyclotron line seems likely. There are two possibilities. There may be a cyclotron absorption feature at approximately 42 keV, and a possible second one at approximately 80 keV. In particular there may be a rather broad absorption feature between the spectral break (25 keV) and approximately 40 keV.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 331-345
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  • 33
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    Gamma ray spectroscopy in astrophysics: Solar gamma ray astronomy on solar maximum mission (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The SMM gamma ray experiment and the important scientific capabilities of the instrument are discussed. The flare size detectable as a function of spectrum integration time was studied. A preliminary estimate indicates that a solar gamma ray line at 4.4 MeV one-fifth the intensity of that believed to have been emitted on 4 August 1972 can be detected in approximately 1000 sec with a confidence level of 99%.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 558-574
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  • 34
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    Search for broad gamma ray lines with the UCR double Compton scatter telescope (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The operation of a double scatter telescope and the evaluation of data obtained during a 24 hour balloon flight are discussed. An increase in gamma rays was observed as the galactic anti-center crossed the aperature of the telescope. Searches for lines from p(n,gamma)d at 2.2 MeV, C-12* at 4.4 MeV and on -16* at 6.1 MeV and for other lines broadened or redshifted are being conducted to identify the processes responsible for the production of celestial gamma rays. Two upper limits for lines in the angalactic anti-center direction at 4.4 MeV and 6.1 MeV are 6 and 4 x 10 to the minus 4 power gamma/sq cm-s.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 217-222
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  • 35
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    Nuclear gamma rays from stellar flares (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Solar flare observations are consistent with the phenomenological description that a loop of magnetic flux is convected to the surface of the star and twisted. The resulting inductive current parallel to the field is dissipated at an enhanced rate throughout the field volume by current limiting instabilities. The steady state balance between joule heating and thermal conduction along the field lines of force to the denser, cooler surface establishes a temperature distribution. The expansion of heated and ionized surface layers leads to a pressure balance and hence predictable density and X-ray emission measure. The current limitation instabilities result observationally in the parallel current being transferred to run-away ions that reach a kinetic energy of some finite fraction of the inductive potential drop. The nuclear excitation gamma rays produced by such a run-away ion current are calculated for a white dwarf flare.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 149-167
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  • 36
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    Mechanisms and sites for astrophysical gamma ray line production (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The production of gamma ray lines and estimates of line fluxes resulting from nuclear deexcitations, positron annihilation, and electron capture at various astrophysical sites are discussed. Supernova and nova explosions synthesize long-lived radioactive isotopes and eject them into space where they produce observable gamma ray lines by decaying into excited levels of daughter nuclei or by emitting positrons. Energetic charged particles in the interstellar medium, in supernova remants, in solar or stellar flares, and possibly in the vicinity of compact objects, produce gamma-ray lines by inelastic collisions which either excite nuclear levels or produce positrons and neutrons. Energetic particles can result from acceleration in time-varying magnetic fields (solar flares) or from gravitational accretion onto neutron stars and black holes. Electromagnetic processes in the strong magnetic fields of pulsars can produce positron-electron pairs, with line emission resulting from positron annihilation. Deexcitations of quantized states in strong magnetic fields can also produce lines.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 7-41
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  • 37
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    The transfer of cyclotron lines through the magnetospheric shell of Hercules X-1 (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Cyclotron emission from a strong magnetic field, has been proposed to identify line feature observed in the hard X-ray spectrum of the neutron star Hercules X-1. If this interpretation is indeed correct, and if the model wherein the 1.24 second hard X-ray pulse is due to the occultation of a more isotropic X-ray flux by an opaque magnetospheric shell is accepted then these observations can be used to place strict limits on the total source luminosity of the cyclotron emission. The observational fate of cyclotron line photons that have emerged from the region near the neutron star surface, but have yet to encounter an opaque shell at the magnetosphere is discussed. It is shown that if a narrow line is incident on such a shell, then a residual narrow feature can emerge from the shell.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 418-424
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  • 38
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    Low energy gamma ray observations with the MPI-Compton telescope (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Although the evaluation of data from the first balloon-flight of a large area Compton telescope is incomplete, two preliminary results are discussed. From the measured background spectrum at float altitude, the sensitivity of the telescope for the detection of cosmic gamma ray lines is estimated. The energy spectra is determined for an enhanced gamma ray flux observed from the direction of the Seyfert galaxy NGC 4151. A schematic drawing of the telescope is presented and discussed.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 207-216
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  • 39
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    Detection of 511 keV positron annihilation radiation from the galactic center direction (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: A balloon-borne gamma ray telescope with an approximately 130 cu cm high purity germanium detector was flown over Australia to detect sharp spectral features from the galactic center direction. A 511 keV positron annihilation line was observed at a flux level of (1.21 plus or minus 0.22) x (10/cu cm) photons/sec/sp cm. Suggestive evidence for the detection of the three-photon positronium continuum is presented. The possible origin of the positrons is discussed.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 169-189
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  • 40
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    Computer simulation of the velocity diffusion of cosmic rays (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Monte Carlo simulation experiments have been performed in order to study the velocity diffusion of charged particles in a static turbulent magnetic field. By following orbits of particles moving in a large ensemble of random magnetic field realizations with suitably chosen statistical properties, a pitch-angle diffusion coefficient is derived. Results are presented for a variety of particle rigidities and rms random field strengths and compared with the predictions of standard quasi-linear theory and the nonlinear partially averaged field theory.
    Schlagwort(e): SPACE RADIATION
    Materialart: Physics of Fluids; 21; Mar. 197
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  • 41
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    Notes on the transonic indicial method (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 16; June 197
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  • 42
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    Acceleration of protons at 32 Jovian radii in the outer magnetosphere of Jupiter (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: A rapid ten-fold increase of proton flux was observed at 32 Jovian radii in Jupiter's outer magnetosphere. The total event lasted about 30 minutes and was composed of many individual events. Both before and after the event, proton flux was similar to the low-flux level found between crossings of the magnetic equator. Measurements of angular distributions and the time histories of proton and alpha particle channels at different energies indicate that the flux increase is caused by local acceleration. It is suggested that the average particle population in the outer magnetosphere is caused by a state of dynamic equilibrium between acceleration and loss processes.
    Schlagwort(e): SPACE RADIATION
    Materialart: Journal of Geophysical Research; 83; Mar. 1
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  • 43
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    Partially averaged field approach to cosmic ray diffusion (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: A new nonlinear technique is used to derive the kinetic equation for particles interacting with turbulent fluctuations. Difficulties associated with quasi-linear theory are avoided. The new method evaluates the effects of the fluctuations along particle orbits which themselves include the effects of a statistically averaged subset of the possible configuration of the turbulence. As an illustration, the pitch-angle diffusion coefficient is calculated for particles interacting with 'slab model' magnetic turbulence, i.e., magnetic fluctuations linearly polarized transverse to a mean magnetic field. The pitch-angle diffusion coefficient is determined in the vicinity of 90-deg pitch angles where quasi-linear theory breaks down. The spatial diffusion coefficient parallel to a mean magnetic field is evaluated by use of the calculated pitch-angle diffusion coefficient. It is suggested that the partially averaged field method is not limited to small amplitude fluctuating fields and hence is not a perturbation theory.
    Schlagwort(e): SPACE RADIATION
    Materialart: Physics of Fluids; 21; Mar. 197
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  • 44
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    Effect of the Mott cross section on the determination of the charge of ultraheavy cosmic rays from emulsion tracks (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Energy deposition due to secondary electrons is calculated as a function of distance from the axis of the track of a heavy ion. The calculation incorporates the empirical formulas of Kobetich and Katz (1968) for delta-ray energy dissipation. Both the Mott and Born-approximation expressions for the delta-ray energy distributions are used, and the results are compared. The energy deposition projected along a line perpendicular to the track is also calculated. These results are used to estimate the effect that the use of the Mott cross section would have in the interpretation of photometric measurements on emulsion tracks of trans-iron cosmic-ray particles. It is shown that the use of 50 keV as a characteristic track-formation electron energy to estimate the effect of the Mott cross section systematically overestimates charge as derived from emulsions for Z greater than 20.
    Schlagwort(e): SPACE RADIATION
    Materialart: Physical Review D - Particles and Fields; vol. 18
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  • 45
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    Gamma-ray astronomy and the origin of cosmic rays (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Recent observations of cosmic gamma radiation are reviewed. It is shown that this radiation consists of an extragalactic background as well as a bright band of galactic radiation lying in the plane of the Milky Way and produced primarily by cosmic-ray collisions with interstellar gas atoms. The galactic gamma radiation is divided into a near component apparently associated with Gould's belt and a far component originating about 15,000 light years away and narrowly confined to the galactic plane. A Great Galactic Ring is identified which is 35,000 light years in diameter and in which most galactic cosmic rays are produced and supernovae and pulsars are concentrated. The physical mechanisms responsible for the production of most of the cosmic gamma rays in the Galaxy are examined, and the origin of galactic cosmic rays is considered. It is concluded that the cosmic rays are produced either in supernova explosions or in the pulsars they leave behind
    Schlagwort(e): SPACE RADIATION
    Materialart: American Scientist; 66; Sept-Oct
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  • 46
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    The cosmic gamma-ray background from the annihilation of primordial stable neutral heavy leptons (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: The spectra and intensities of gamma radiation from (1) a homogeneous cosmic lepton background (2) a possible lepton halo around the Galaxy, and (3) integrated background radiation from possible lepton halos around other galaxies and from rich galaxy clusters are examined. Heavy-lepton annihilation radiation from the halos of other galaxies accounts for at most 0.005 of the background intensity, and the radiation from rich clusters account for at most 0.00005 of the background intensity. It is suggested that lepton annihilation fluxes from a galactic halo would be confused with cosmic-ray produced radiation and would therefore be difficult to observe. Radiation from a homogeneous cosmological lepton background might account for approximately 0.0001 of the observed cosmic gamma ray background. Energy spectrum and isotropy are considered.
    Schlagwort(e): SPACE RADIATION
    Materialart: Astrophysical Journal; vol. 223
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  • 47
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    Observations of medium-energy gamma-ray emission from the galactic center region (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Measurements of the gamma-ray emission in the medium-energy range between 15 and 100 MeV, obtained during two balloon flights from Brazil, are presented. The importance of this energy region in determining whether neutral-pion decay or electron bremsstrahlung is the most likely dominant source mechanism is discussed, along with the implications of such observations. Specifically, the data from this experiment suggest that emission from the galactic plane is similar to the theoretical spectrum calculated by Fichtel et al. (1976), including both source mechanisms but with the bremsstrahlung component enhanced by a factor of about 2. A spectral distribution of gamma-rays produced in the residual atmosphere above the instrument is also presented and compared with other data. A rather smooth spectral variation from high to low energies is found for the atmospheric spectrum.
    Schlagwort(e): SPACE RADIATION
    Materialart: Astrophysical Journal; vol. 225
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  • 48
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    Summary of system state-of-health measurements STRATCOM 8: A balloon experiment (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Goddard Space Flight Center STRATCOM 8 Data Workshop and Suppl.; p 24-31
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  • 49
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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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    Publikationsdatum: 2011-08-17
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Goddard Space Flight Center STRATCOM 8 Data Workshop and Suppl.; p 10-23
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  • 50
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    Ames collaborative study of cosmic ray neutrons - Mid-latitude flights (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Three aircraft flights at 12.5 km have yielded data on cosmic-ray neutron-flux densities, neutron dose equivalent rates, and exposure rates for ionizing radiation. The data, collected at 45, 38, and 48 degrees N, indicate: (1) neutron dose equivalent rates of 0.20, 0.14, and 0.22 mrem/hour, (2) exposure rates from the ionizing component of 0.37, 0.31, and 0.41 mR/hour, (3) that the dose equivalent from 3-13-MeV neutrons is 30% of the total for all neutrons, (4) that exposure rates decrease exponentially with decreasing pressure altitude with a 140 g/sq cm attenuation length at 43 degrees N geomagnetic latitude, and (5) that the ionizing component of cosmic ray secondaries is less sensitive to latitude changes than the neutron component.
    Schlagwort(e): SPACE RADIATION
    Materialart: Health Physics; 34; Apr. 197
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  • 51
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    New limits on gamma-ray bursts (1978)
    In:  Other Sources
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    Publikationsdatum: 2011-08-17
    Beschreibung: Two balloon flights of large-area scintillation crystal detector arrays indicate that the rate of weak gamma-ray bursts is significantly below that expected from a uniform distribution of burst sources. This result, combined with the data from stronger bursts, gives strong evidence for a galactic confinement of burst sources. Reasonable models of confinement limit the intrinsic radiated energy per burst to the order of 10 to the (39th to 41st power) ergs.
    Schlagwort(e): SPACE RADIATION
    Materialart: Astrophysical Journal; vol. 223
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  • 52
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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
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 259-286
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  • 53
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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
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 227-258
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  • 54
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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
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 201-226
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  • 55
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    Wind tunnel evaluation of YF-12 inlet response to internal airflow disturbances with and without control (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Dryden Flight Res. Center YF-12 Experiments Symp., Vol. 1; p 157-192
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  • 56
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    Pilot Workload Measurement and Experience on Supersonic Cruise Aircraft (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 121-134
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  • 57
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    The YF-12 Gust Velocity Measuring System (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 135-154
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  • 58
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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
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 97-119
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  • 59
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    Flight-Measured Aerodynamic Loads on a 0.92 Aspect Ratio Lifting Surface (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 73-91
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  • 60
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    Overview of the NASA YF-12 program (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 3-25
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  • 61
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    Recent Load Calibrations Experience with the YF-12 Airplane (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: YF-12 Experiments Symp., Vol. 1; p 47-72
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  • 62
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    Wake vortex technology (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: CTOL Transport Technol., 1978; p 757-771
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  • 63
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    Development of advanced stability theory suction prediction techniques for laminar flow control (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: CTOL Transport Technol. 1978; p 375-394
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  • 64
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    Laminar flow control overview (1978)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: CTOL Transport Technol., 1978; p 349-356
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  • 65
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    An analysis of prop-fan/airframe aerodynamic integration (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-152186 , NAS 1.26:152186 , D6-47113
    Format: application/pdf
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  • 66
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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
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-152160 , NEAR-TR-160
    Format: application/pdf
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  • 67
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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
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2948 , AR-76-3
    Format: application/pdf
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  • 68
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    A computer program to calculate the longitudinal aerodynamic characteristics of upper-surface-blown wing-flap configurations (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-3005 , NEAR-TR-158
    Format: application/pdf
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  • 69
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    Static tests of the J97 powered, external augmenter V/STOL wind tunnel model (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-152403 , DHC-DND-77-4
    Format: application/pdf
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  • 70
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    Steady state spurious errors in shock-capturing numerical schemes (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: KTH-AERO-TN-60 , TRITA-FPT-032
    Format: application/pdf
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  • 71
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    The aerodynamic design of an advanced rotor airfoil (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2961 , LG77ER0208
    Format: application/pdf
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  • 72
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    Interaction of a two-dimensional strip boundary layer with a three-dimensional transonic swept-wing code (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78640
    Format: application/pdf
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  • 73
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    Towards complete configurations using an embedded grid approach (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-3030
    Format: application/pdf
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  • 74
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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
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-145362 , CRINC-FRL-266-2
    Format: application/pdf
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  • 75
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    Design and analytical study of a rotor airfoil (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2988 , D210-11239-1
    Format: application/pdf
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  • 76
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    Aerodynamic preliminary analysis system. Part 1: Theory (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-145284
    Format: application/pdf
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  • 77
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    Data analysis for the hard X-ray experiment on board the ANS spacecraft (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An analysis of X ray bursts form globular clusters gathered by the Astronomical Netherlands Satellite is presented. Publications were prepared on the cosmic ray induced environment, and maps of these radiations as functions of latitude and longitude were generated.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA-CR-166682
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  • 78
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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
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-159001
    Format: application/pdf
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  • 79
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    Flap survey test of a combined surface blowing model: Flow measurements at static flow conditions (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-152124
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  • 80
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    Numerical solution of the Navier-Stokes equations for arbitrary blunt bodies in supersonic flows (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: Numerical Heat Transfer; 1; Oct
    Format: text
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  • 81
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    The dynamical halo and the variation of cosmic-ray path length with energy (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: It is shown that the dynamical halo model offers a natural explanation for the form of the variation of the cosmic-ray path length with energy. The variation above approximately 1 GeV/nucleon can be understood as due to the variation of the diffusion coefficient, and hence the resident time, with energy. The flattening of the curve below 1 GeV/nucleon is seen to mark a transition to a convection dominated regime where coefficient is no longer the determining parameter. A fit to the observations yields a halo outflow velocity of 8 km sec/1. An attempt is made to determine the overall scale of the halo and the diffusion coefficient using recent Be-10 flux measurements but the data do not agree well enough to pin down these variables to within less than four or five orders of magnitude.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA-TM-79647
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  • 82
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    Comparison of concurrent strain gage- and pressure transducer-measured flight loads on a lifting reentry vehicle and correlation with wind tunnel predictions (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Concurrent strain gage and pressure transducer measured flight loads on a lifting reentry vehicle are compared and correlated with wind tunnel-predicted loads. Subsonic, transonic, and supersonic aerodynamic loads are presented for the left fin and control surfaces of the X-24B lifting reentry vehicle. Typical left fin pressure distributions are shown. The effects of variations in angle of attack, angle of sideslip, and Mach number on the left fin loads and rudder hinge moments are presented in coefficient form. Also presented are the effects of variations in angle of attack and Mach number on the upper flap, lower flap, and aileron hinge-moment coefficients. The effects of variations in lower flap hinge moments due to changes in lower flap deflection and Mach number are presented in terms of coefficient slopes.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-1331 , H-1035
    Format: application/pdf
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  • 83
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    Effects of wing leading-edge deflection on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Wing leading-edge deflection effects on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration were determined. Static force tests were conducted in a V/STOL tunnel at a Reynolds number of about 2.5 x 1 million for an angle-of-attack range from -10 deg to 17 deg and an angle-of-sideslip range from -5 deg to 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78787
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  • 84
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    Laser-velocimeter surveys of merging vortices in a wind tunnel: Complete data and analysis (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The merger of two corotating vortices was studied with a laser velocimeter designed to measure the two cross-stream components of velocity. Measurements were made at several downstream distances in the vortex wake shed by two semispan wings mounted on the wind-tunnel walls. The velocity data provided wall-defined contours of crossflow velocity, stream function, and vorticity for a variety of test conditions. Downstream of the merger point, the vorticity was found to be independent of the downstream distance for radii smaller than r/b = 0.05. For larger radii, the vorticity depended on the distance from the wing. Upstream of the merger, a multicell vorticity pattern was found.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78449 , A-7262
    Format: application/pdf
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  • 85
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    Aerodynamic derivatives for an oblique wing aircraft estimated from flight data by using a maximum likelihood technique (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: There are several practical problems in using current techniques with five degree of freedom equations to estimate the stability and control derivatives of oblique wing aircraft from flight data. A technique was developed to estimate these derivatives by separating the analysis of the longitudinal and lateral directional motion without neglecting cross coupling effects. Although previously applied to symmetrical aircraft, the technique was not expected to be adequate for oblique wing vehicles. The application of the technique to flight data from a remotely piloted oblique wing aircraft is described. The aircraft instrumentation and data processing were reviewed, with particular emphasis on the digital filtering of the data. A complete set of flight determined stability and control derivative estimates is presented and compared with predictions. The results demonstrated that the relatively simple approach developed was adequate to obtain high quality estimates of the aerodynamic derivatives of such aircraft.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-1336 , H-1003
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  • 86
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    Derivation and evaluation of an approximate analysis for three-dimensional viscous subsonic flow with large secondary velocities (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An approximate analysis is presented for calculating three-dimensional, low Mach number, laminar viscous flows in curved passages with large secondary flows and corner boundary layers. The analysis is based on the decomposition of the overall velocity field into inviscid and viscous components with the overall velocity being determined from superposition. An incompressible vorticity transport equation is used to estimate inviscid secondary flow velocities to be used as corrections to the potential flow velocity field. A parabolized streamwise momentum equation coupled to an adiabatic energy equation and global continuity equation is used to obtain an approximate viscous correction to the pressure and longitudinal velocity fields. A collateral flow assumption is invoked to estimate the viscous correction to the transverse velocity fields. The approximate analysis is solved numerically using an implicit ADI solution for the viscous pressure and velocity fields. An iterative ADI procedure is used to solve for the inviscid secondary vorticity and velocity fields. This method was applied to computing the flow within a turbine vane passage with inlet flow conditions of M = 0.1 and M = 0.25, Re = 1000 and adiabatic walls, and for a constant radius curved rectangular duct with R/D = 12 and 14 and with inlet flow conditions of M = 0.1, Re = 1000, and adiabatic walls.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-159430 , UTRC78-106
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  • 87
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    Upper limits on the cyclotron lines from Her X-1 as observed with OSO-8 (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Observations of Her X-1 were obtained during its ON-state in September, 1977, with the high-energy X-ray detector on board OSO-8. Upper limits on the line fluxes at 60 and 135 keV based on these observations are above, and hence consistent with, the positive results reported by Trumper, et al from a balloon flight during the same time interval. A detailed analysis of the time-variable et al background spectrum suggests that the line emission, especially in the time-averaged spectrum of Her X-1 previously reported by other workers at 25, 60, and 135 keV, is due to instrumental effects. The spectrum obtained with OSO-8 in September, 1977, is considerably steeper than that observed in pre-1976 balloon flights. These results are consistent with the results obtained by Trumper showing a decrease in the effective temperature of Her X-1 between May, 1976, and September, 1977.
    Schlagwort(e): SPACE RADIATION
    Materialart: ma Ray Spectry. In Astrophys.; p 371-385
    Format: text
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  • 88
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    The galactic gamma-ray flux in the 0.06 to 5 MeV range (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Gamma ray emission from the longitude range -50 deg less than or equal to lambda less than or equal to 22 deg recorded by the Apollo gamma-ray spectrometer and by individual observers is discussed. Agreement of the galactic emission spectra near 1 MeV with hard X-ray observations of the galactic central regions suggests that an ensemble of point sources is responsible for the emissions. Apollo 16 upper limits to the cosmic 4.4 MeV line flux imply that the ratio of line strength to continuum emission for the region observed by Haymes et al is higher than the galactic average.
    Schlagwort(e): SPACE RADIATION
    Materialart: Gamma Ray Spectry. in Astrophys.; p 190-206
    Format: text
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  • 89
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    HEAO-1 observations of Her X-1 at energies above 13 keV (1978)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Results from preliminary analysis of HEAO-1 pointing observations of Her X-1 on three days in February 1978 are presented. Pulsed flux is detected up to approximately 70 keV with a clear indication of emission at approximately 60 deV which is above the continuum spectrum extrapolated from lower energies. If this excess emission is interpreted as a spectral line, its intensity varies from (1.2 plus or minus 0.2) x (10 to the minus 3 power) to (0.2 plus or minus 0.2) x (10 to the minus 3 power) ph/sq cm-sec with a time scale of one day. A factor 2 decrease in the low energy continuum is associated with the decrease in the excess emission.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA. Goddard Space Flight Center Gamma Ray Spectry. in Astrophys.; p 386-393
    Format: text
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  • 90
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    Analysis of stability contributions of high dihedral V-tails (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation was undertaken to determine the effectiveness of four analytical methods (empirical, modified empirical, vortex-lattice, and an inviscid, three dimensional, potential flow, wing body program) to estimate the lateral and longitudinal static stability characteristics of an isolated V-tail wind tunnel model. The experimental tests were conducted in the V/STOL tunnel at a Mach number of 0.18. Angle-of-attack data were obtained from -12 deg to 8 deg at 0 deg sideslip. Sideslip sweeps from -5 deg to 10 deg were made at angles of attack of 4 deg, 0 deg and -4 deg. The V-tail dihedral angles were 45 deg, 50 deg, 55 deg, and 60 deg.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78729 , AVRADCOM-TR-78-34 , L-12277
    Format: application/pdf
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  • 91
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    Control-surface hinge-moment calculations for a high-aspect-ratio supercritical wing (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The hinge moments, at selected flight conditions, resulting from deflecting two trailing edge control surfaces (one inboard and one midspan) on a high aspect ratio, swept, fuel conservative wing with a supercritical airfoil are estimated. Hinge moment results obtained from procedures which employ a recently developed transonic analysis are given. In this procedure a three dimensional inviscid transonic aerodynamics computer program is combined with a two dimensional turbulent boundary layer program in order to obtain an interacted solution. These results indicate that trends of the estimated hinge moment as a function of deflection angle are similar to those from experimental hinge moment measurements made on wind tunnel models with swept supercritical wings tested at similar values of free stream Mach number and angle of attack.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78664 , L-12219
    Format: application/pdf
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  • 92
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    Performance with and without inlet radial distortion of a transonic fan stage designed for reduced loading in the tip region (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A transonic compressor stage designed for a reduced loading in the tip region of the rotor blades was tested with and without inlet radial distortion. The rotor was 50 cm in diameter and designed for an operating tip speed of 420 m/sec. Although the rotor blade loading in the tip region was reduced to provide additional operating range, analysis of the data indicates that the flow around the damper appears to be critical and limited the stable operating range of this stage. For all levels of tip and hub radial distortion, there was a large reduction in the rotor stall margin.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-1294 , E-9246
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  • 93
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    Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The static aerodynamic characteristics of a 1/30 scale model of a wing-body concept for a high speed research airplane were investigated in the Langley 20 inch Mach six tunnel. The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was six at a Reynolds number, based on model fuselage length, of about 13,700,000. The test angle-of-attack range was 4 to 20 D at constant angles of sideslip of 0, 2, and 4 deg. The elevons were deflected from 10 to -15 D for pitch control. Roll and yaw control were investigated. Experimental aerodynamic characteristics are compared with analytical elements.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-1249 , L-12183
    Format: application/pdf
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  • 94
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    Rotary balance data for a typical single-engine low-wing general aviation design for an angle-of-attack range of 30 deg to 90 deg (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Aerodynamic characteristics obtained in a spinning flow environment utilizing a rotary balance located spin tunnel are presented in plotted form for a 1/5 scale single-engine low-wing general aviation airplane model. The configurations tested include the basic airplane, various airfoil shapes, tail designs, fuselage strakes and modifications as well as airplane components. Data are presented for pitch and roll angle ranges of 30 to 90 degrees and 10 to -10 degrees, respectively, and clockwise and counter-clockwise rotations covering an Omega b/2V range from 0 to .9. The data are presented without analysis.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2972
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  • 95
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    REXOR 2 rotorcraft simulation model. Volume 3: User's manual (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N78-30042.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-145333 , LR-28435-VOL-3
    Format: application/pdf
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  • 96
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    REXOR 2 rotorcraft simulation model. Volume 1: Engineering documentation (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A rotorcraft nonlinear simulation called REXOR II, divided into three volumes, is described. The first volume is a development of rotorcraft mechanics and aerodynamics. The second is a development and explanation of the computer code required to implement the equations of motion. The third volume is a user's manual, and contains a description of code input/output as well as operating instructions.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-145331 , LR-28435-VOL-1
    Format: application/pdf
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  • 97
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    The annihilation of galactic positrons (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The probabilities of various channels of galactic positron annihilation were evaluated and the spectrum of the resulting radiation was calculated. The narrow width (FWHM less than 3.2 keV) of the 0.511 MeV line observed from the galactic center implies that a large fraction of positrons should annihilate in a medium of temperature less than 100,000 K and ionization fraction greater than 0.05. HII regions at the galactic center could be possible sites of annihilation.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA-TM-79600
    Format: application/pdf
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  • 98
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    Observability of the neutrino flux from the inner region of the galactic disk (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The observability of galactic neutrinos in a detector of 10 billion tons of water with an observing time of a few years is explored. Although the atmospheric flux exceeds the galactic flux considerably at energies greater than or equal to 1 TeV, the latter may still provide a marginally observable signal owing to its directionality. Galactic muon neutrinos with energy greater than or equal to 1 TeV will produce a signal approximately 2 sigma above the atmospheric background over a four year period. If electron neutrinos can also be studied with the deep underwater muon and neutrino detector, then galactic electron neutrinos above 1 TeV would give an approximate 4 to 5 sigma signal above the electron neutrino background over a four year integration time.
    Schlagwort(e): SPACE RADIATION
    Materialart: NASA-TM-79658
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  • 99
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    Static performance of five twin-engine nonaxisymmetric nozzles with vectoring and reversing capability (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Transonic tunnel test was performed to determine the static performance of five twin-engine nonaxisymmetric nozzles and a base-line axisymmetric nozzle at three nozzle power settings. Static thrust-vectoring and thrust-reversing performance were also determined. Nonaxisymmetric-nozzle concepts included two-dimensional convergent-divergent nozzles, wedge nozzles, and a nozzle with a single external-expansion ramp. All nonaxisymmetric nozzles had essentially the same statis performance as the axisymmetric nozzle. Effective thrust vectoring and reversing was also achieved.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-1224 , L-12067
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  • 100
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    Wing analysis using a transonic potential flow computational method (1978)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The ability of the method to compute wing transonic performance was determined by comparing computed results with both experimental data and results computed by other theoretical procedures. Both pressure distributions and aerodynamic forces were evaluated. Comparisons indicated that the method is a significant improvement in transonic wing analysis capability. In particular, the computational method generally calculated the correct development of three-dimensional pressure distributions from subcritical to transonic conditions. Complicated, multiple shocked flows observed experimentally were reproduced computationally. The ability to identify the effects of design modifications was demonstrated both in terms of pressure distributions and shock drag characteristics.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-78464 , A-7308
    Format: application/pdf
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