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  • Other Sources  (728)
  • AERODYNAMICS  (415)
  • INSTRUMENTATION AND PHOTOGRAPHY  (313)
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  • Life and Medical Sciences
  • 2005-2009
  • 1975-1979  (728)
  • 1925-1929
  • 1975  (728)
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  • 2005-2009
  • 1975-1979  (728)
  • 1925-1929
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  • 1
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    Computational aerodynamics (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The application of computer techniques for solving Navier-Stokes equations in support of wind tunnel tests is discussed. The ILLIAC IV computer is considered for this purpose and its limitations are analyzed. The author states that improved computers will make it possible to solve many aerodynamic problems and reduce the amount of wind tunnel testing required for adequate data processing.
    Keywords: AERODYNAMICS
    Type: NASA/Univ. Conf. on Aeron.; p 211-212
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  • 2
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    On wake vortex alleviation (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Research within NASA relating to the nature of lift-induced vortex wakes behind large aircraft and the means whereby the hazard they represent to smaller aircraft can be alleviated is reviewed. The research, carried out in ground based facilities and in flight shows that more rapid dispersion of the wake can be effected by several means and that the modification of span-loading by appropriate flap deflection holds promise of early practical application.
    Keywords: AERODYNAMICS
    Type: NASA/Univ. Conf. on Aeron.; p 143-168
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  • 3
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    An experimental and numerical investigation of shock wave induced turbulent boundary layer separation at hypersonic speeds (1975)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: A thoroughly documented experiment is reported that was specifically designed to test and guide computations of the interaction of an impinging shock wave with a turbulent boundary layer. Detailed mean flow field and surface data are presented for two shock strengths which resulted in attached and separated flows, respectively. Numerical computations are used to illustrate the dependence of the computations on the particulars of the turbulence models. Models appropriate for zero pressure gradient flows predicted the overall features of the flow fields, but were deficient in predicting many of the details of the interaction regions. Improvements to the turbulence model parameters were sought through a combination of detailed data analysis and computer simulations which tested the sensitivity of the solutions to model parameter changes. Computer simulations using these improvements are presented and discussed.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 13 p
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  • 4
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    On the calculation of supersonic separating and reattaching flows (1975)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: A method is developed for solving the laminar and turbulent compressible boundary layer equations for separating and reattaching flows. Results of this method are compared with experimental data for two laminar and three turbulent layer, shock wave interactions. Several Navier-Stokes solutions are obtained for each of the laminar boundary layer, shock wave interactions considered. Comparison of these solutions indicates a first order sensitivity in C sub f to the computational mesh selected in both the viscous and inviscid portions of the flow. Comparison of the present boundary layer solutions with the Navier-Stokes solutions and with data for a given Mach number indicates that as long as the separation bubble is small, the boundary layer approximation yields solutions whose accuracy is comparable to the Navier-Stokes solutions.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 12 p
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  • 5
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    The transformation of aerodynamic stability derivatives by symbolic mathematical computation (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The formulation of mathematical models of aeronautical systems for simulation or other purposes, involves the transformation of aerodynamic stability derivatives. It is shown that these derivatives transform like the components of a second order tensor having one index of covariance and one index of contravariance. Moreover, due to the equivalence of covariant and contravariant transformations in orthogonal Cartesian systems of coordinates, the transformations can be treated as doubly covariant or doubly contravariant, if this simplifies the formulation. It is shown that the tensor properties of these derivatives can be used to facilitate their transformation by symbolic mathematical computation, and the use of digital computers equipped with formula manipulation compilers. When the tensor transformations are mechanised in the manner described, man-hours are saved and the errors to which human operators are prone can be avoided.
    Keywords: AERODYNAMICS
    Type: Aeronautical Quarterly; 26; May 1975
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  • 6
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    An aneroid pressure sensor for constant-level balloons (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The pressure sensor for the Tropical Wind Energy conversion and Reference Level Experiment (TWERLE) is described. Key design features of the sensor are: capacitive coupling, reference at midrange, up-down counting, passive oven, storage at flight pressure and prelaunch calibration. Sensor specifications are given which are based on the production results of 440 units. Drift, as estimated from simulated life tests, is 1 mb per 6 months. The overall weight of the sensor, including thermal package, is 180 g.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Applied Meteorology; 14; Sept
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  • 7
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    The low frequency sound from multipole sources in axisymmetric shear flows, with applications to jet noise (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A closed-form solution for the sound radiation from multipole sources imbedded in an infinite cylindrical jet with an arbitrary velocity profile is obtained. It is valid in the limit where the wavelength is large compared with the jet radius. Simple formulae for the acoustic pressure field due to convected point sources are also obtained. The results show (in a simple way) how the mean flow affects the radiation pattern from the sources. For convected lateral quadrupoles it causes the exponent of the Doppler factor multiplying the far-field pressure signal to be increased from the value of 3 used by Lighthill to 5.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 70; Aug. 12
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  • 8
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    Infrared upconversion as a means of seeing in the dark (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A new approach to seeing in the dark is described which is based on the principles of nonlinear optics employing a crystal such as lithium iodate. A nonlinear optical device capable of producing photons at higher frequencies from lower-frequency incident light is shown to upconvert infrared light directly into visible light. The major advantages of the infrared upconversion process is that it permits the infrared signal to be detected by photon-counting devices presently available for the visible spectral region, and that it can provide sensitivity to infrared radiation without the need for cryogenic cooling of the detector used. Early works on infrared upconversion are reviewed. The development of applications is discussed as to astronomical spectroscopy and infrared image upconversion involving either angular or positional resolution elements. The demonstration of infrared upconversion in rectangular waveguides of single-crystal GaAs by Anderson et al. (1971) indicates future possibilities in upconversion by the use of integrated optics devices.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Sciences Center Newsletter; 9; May 1975
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  • 9
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    An infrared heterodyne radiometer for high-resolution measurements of solar radiation and atmospheric transmission (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A tunable, Dicke-switched, infrared heterodyne radiometer (IHR) has been designed, fabricated, tested, and used to observe solar radiation and determine the atmospheric transmissivity in the 9-11-micron spectral band. The IHR provides a spectral resolution of 0.0067 reciprocal cm, a minimum detectable power level of 2.9 times ten to the minus twenty-third power W/Hz, and a temperature resolution of less than 1 K for a source temperature of 1000 K, an IF predetection bandwidth of 100 MHz, and an integration time of 30 s. Detailed design equations and measured IHR performance are presented. The IHR was used to make solar and atmospheric transmission measurements, and a vertical-path atmospheric attenuation of 2.3 dB has been established under favorable weather conditions. The attenuation of solar radiation due to cloud cover and haze has also been investigated.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Journal of Quantum Electronics; QE-11; Aug. 197
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  • 10
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    The Viking Mars lander camera (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The 7.3 kg cameras for the 1976 Viking Mars expedition feature an array of 12 silicon photodiodes, including six spectral bands for color and near-infrared imaging with an angular resolution of 0.12 deg and four focus steps for broadband imaging, with an improved angular resolution of 0.04 deg. The field of view in elevation ranges from 40 deg above to 60 deg below the horizon, and in azimuth ranges to 342.5 deg. The cameras are mounted 0.8 m apart to provide a stereo view of the area accessible to a surface sampler for biological and chemical investigations. The scanning rates are synchronized to the lander data transmission rates of 16000 bits per sec to the Viking orbiters as relay stations and 250 bits per sec directly to earth. However, image data can also be stored on a lander tape recorder. About 10 million bits of image data will be transmitted during most days of the 60-day-long mission planned for each lander.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Space Science Instrumentation; 1; May 1975
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  • 11
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    The Pioneer XI high field fluxgate magnetometer (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The high field fluxgate magnetometer experiment flown aboard the Pioneer XI spacecraft is described. This extremely simple instrument was used to extend the spacecraft's upper-limit measurement capability by approximately an order of magnitude (from 0.14 mT to 1.00 mT) with minimum power and volume requirements. This magnetometer was designed to complement the low-field measurements provided by a helium vector magnetometer and utilizes magnetic ring core sensors with biaxial orthogonal sense coils. The instrument is a single-range, triaxial-fluxgate magnetometer capable of measuring fields of up to 1 mT along each orthogonal axis, with a maximum resolution of 1 microT.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Space Science Instrumentation; 1; May 1975
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  • 12
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    Effect of grid transparency and finite collector size on determining ion temperature and density by the retarding potential analyzer (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The effects of the grid transparency and finite collector size on the values of thermal ion density and temperature determined by the standard RPA (retarding potential analyzer) analysis method are investigated. The current-voltage curves calculated for varying RPA parameters and a given ion mass, temperature, and density are analyzed by the standard RPA method. It is found that only small errors in temperature and density are introduced for an RPA with typical dimensions, and that even when the density error is substantial for nontypical dimensions, the temperature error remains minimum.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Geophysical Research; 80; June 1
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  • 13
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    Phase correction for a Michelson interferometer with misaligned mirrors (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The phase correction for a Michelson interferometer with misaligned mirrors in converging light is shown to give rise to a quadratic phase shift. In general, the calculation of a spectrum from the measured interferogram needs phase correction. Phase corrections have been well worked out for the cases of a linear phase shift and a phase that is slowly varying. The standard procedures for correcting calculated spectra need to be modified, however, to remove any phase errors resulting from misaligned mirrors.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; June 197
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  • 14
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    Estimates of nonequilibrium radiation for Venus entry (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The present investigation is an analysis of the radiation from the chemical nonequilibrium region in the shock layer about a vehicle during Venus entry. The radiation and the flow were assumed to be uncoupled. An inviscid, nonequilibrium flowfield was calculated and an effective electronic temperature was determined for the predominant radiating species. Species concentrations and electronic temperature were then input into a radiation transport code to calculate heating rates. The present results confirm earlier investigations which indicate that the radiation should be calculated using electronic temperatures for the radiating species. These temperatures are not related in a simple way to the local translational temperature. For the described mission, the nonequilibrium radiative heating rate is approximately twice the corresponding equilibrium value at peak heating.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Apr. 197
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  • 15
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    The Pioneer 10/11 and Helios A/B cosmic ray instruments (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper describes the design and performance of a set of cosmic-ray particle experiments for the Pioneer 10/11 and Helios A/B space missions. These experiments had to be very light-weight, low-power and electronically sophisticated in order to meet the spacecraft and scientific requirements. Both sets of missions use several solid-state detector telescopes to measure protons from 100 KeV to 800 MeV and heavier ions up to Neon at 200 MeV per nucleon. Good performance is required for 7-8 years, and the system must tolerate large vibration loads and ionizing radiation doses up to 500,000 rads.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 16
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    Thermal diffusivity measurements of particulates using the differentiated line source (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A method is described in which thermal diffusivity measurements can be made on particulate materials using the identical instrumentation as described in previous papers for measuring thermal conductivity. The measurements for the two properties can be made simultaneously, thus eliminating the changes in conditions when they are made separately. This system has particular application for studies of simulated lunar, planetary, or asteroidal surfaces in which laboratory measurements can be correlated with astronomical observations of thermal inertia. A representative set of data is shown which gives thermal diffusivity and thermal conductivity measurements on a particulate basalt in which the values for each temperature were taken simultaneously. A value for specific heat is calculated for measurements taken at each temperature.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 46; May 1975
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  • 17
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    Bringing wings of change - NASA's airfoil research program (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A review is presented of progress in attaining technical objectives in three areas of semiautomatic airfoil development: software, hardware, and applications. Software objectives seek improved mathematical models and computer codes for flow analysis and design optimization for a variety of conditions. The 17-step iterative computer model used in designing the GA (W)-1 airfoil is effective but not yet fully automated; with present methods only single-point computer optimization is possible. Hardware objectives calling for improvement in test facilities and techniques are met in part by the introduction of the Langley (F-3C) wind tunnel for independent evaluation of transonic Mach number and Reynolds effects up to 12-16 million, and by a two-dimensional test section for the Langley 1/3 transonic cryogenic tunnel which will extend the Reynolds number to 50 million. The current status of low-speed, thin, and rotorcraft airfoil development programs is discussed.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 13; Oct. 197
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  • 18
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    Apparatus for production, measurement and reaction studies of dissociated gases at elevated temperatures (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An apparatus is described which is used for the controlled production, characterization, and study of dissociated gases in a microwave discharge at elevated temperatures. A unique feature is the ability to produce and study a microwave discharge plasma in the heated zone. This allows elevated temperature reactions to be studied in high concentrations of dissociated gases. Further, the system permits weight change measurements of specimens in the plasma, thus facilitating reaction rate determinations. Included is a description of a cavity for use on a 50-mm diameter cylindrical reactor. The effects of flow rate, pressure, temperature, power, metal sample, and sampling position on dissociation percentage of oxygen in the apparatus are described as well as a technique for sample temperature measurements in the plasma which permits determination of high temperature recombination coefficients and reaction rates.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Transactions on Plasma Science; PS-3; June 197
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  • 19
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    Pulse modulation effect on velocity fringes (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The degradation of a hologram caused by object motion can be utilized to measure the rate of change of the length of an object beam. A rectangular shaped laser pulse is ordinarily used to illuminate the object in such an investigation. The velocity fringes obtained are considered in the calculation. There are no velocity fringes for Gaussian shaped pulses or for the pulses produced by a Q-switched ruby laser. It is shown with the aid of a mathematical analysis that a pulse of oscillating intensity or a pulse train will yield velocity fringes regardless of the shape of an individual pulse.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; May 1975
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  • 20
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    The development of an L-band radiometer dual-mode horn (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An antenna was developed for the remote microwave measurement of ocean surface temperature during a flight test in a C54 aircraft. The basic antenna is a conical dual-mode horn similar to the dual-mode horn described by Potter (1963). The pertinent internal dimensions of the horn are given. The measured E and H plane patterns for the linearly polarized horn for a range of frequencies are shown in a graph.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Transactions on Antennas and Propagation; AP-23; May 1975
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  • 21
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    A new high-speed solar spectrograph for meter and decameter wavelengths (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Solar Physics; 40; Feb. 197
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  • 22
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    Collecting efficiency of a cylindrical mirror electron energy analyzer with pre-retarding lens (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The electron collecting efficiency of a cylindrical mirror energy analyzer incorporating retardation of the electrons prior to analysis has been determined over the range 0 to 30 eV by two methods. The first method requires the use of a vacuum ultraviolet monochromator to produce monoenergetic electrons of different energies; the second method involves measuring the energy-brightness relationship of the retarding optics and should be applicable to any deflection analyzer with pre-retarding optics. The results of the two methods are compared and the limitations of the latter method are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Electron Spectroscopy and Related Phenomena; 6; 1975
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  • 23
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    An all-sky camera for time-resolved lightning photography (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Applied Meteorology; 14; Mar. 197
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  • 24
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    Calibration of a cylindrical RF capacitance probe (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Ambient electron concentrations derived from observations with the Radio Astronomy Explorer 1 antenna capacitance probe have been compared with upper hybrid resonance measurements from the same spacecraft. From this comparison an empirical correction factor for the capacitance probe measurements has been derived. The differences between the two types of measurements is attributed to sheath effects.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Geophysical Research; 80; Feb. 1
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  • 25
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    The use of Whatman-41 filters for high volume air sampling (1975)
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    Publication Date: 2011-08-16
    Description: The feasibility of using W41 filter media on a routine TSP high-volume monitoring network was determined by comparison with glass fiber (GF) filtering. Results indicate that suspended particulate samples from GF filters averaged slightly, but not significantly, higher than those from Whatman-41 filters. Some extra handling procedures were required to avoid errors due to the hygroscopic nature of W41 filters; these added procedures are not overly burdensome, however, and they allow the performance of analytical work, thus extending the capabilities of high-volume sampling. It was demonstrated that W41 filters are practical for air quality monitoring and elemental analysis in environments similar to Cleveland's.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Atmospheric Environment; 9; 1975
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  • 26
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    Infrared heterodyne spectroscopy of astronomical and laboratory sources at 8.5 microns (1975)
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    Publication Date: 2011-08-16
    Description: It is pointed out that the first successful infrared heterodyne spectrometer featuring semituneable semiconductor diode lasers was constructed and used near 8.5 micrometers to make laboratory measurements of line profiles in nitrous oxide and to detect thermal emission from Mars and from the moon. Questions of instrument design are discussed along with the significance of the results obtained in the investigation.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nature; 253; Feb. 13
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  • 27
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    Two high resolution velocity vector analyzers for cosmic dust particles (1975)
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    Publication Date: 2011-08-16
    Description: Two new methods are described to measure velocities and angles of incidence of charged cosmic dust particles with precisions of about 1% and 1 deg, respectively. Both methods employ four one-dimensional position-sensitive detectors in series. The first method utilizes a charge-dividing technique while the second utilizes a time-of-flight technique for determining the position of a particle inside the instrument. The velocity vectors are measured although mechanical interaction between the particle and the instrument is completely avoided. Applications to cosmic dust composition and collection experiments are discussed. The range of radii of measurable particles is from about 0.01 to 100 microns at velocities from 1 to 80 km/sec.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 46; Feb. 197
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  • 28
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    Plastic scintillation counters with an area of 2 sq m (1975)
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    Publication Date: 2011-08-16
    Description: Two designs of plastic scintillation counters with an area of 2 sq m scanned in each case by a single photomultiplier of the FEU-49 type are described. The radial dependence of their light collection at the place of the path of the detected particle does not exceed 10% while the half width of the differential distribution of the pulse amplitudes from nonfiltered cosmic radiation at sea level is 90 to 95%, and 65%, the plastic thickness being 5 cm and 10 cm, respectively. The temperature coefficient of the counter is 0.32% per 1 C.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 389-393
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  • 29
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    Generalization of formulas for ionization energy losses and collision cross section in threshold detectors (1975)
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    Publication Date: 2011-08-16
    Description: Two types of formulas were obtained for (- dE/dx) and the number of collisions per unit of path length (dN/dx) = const, which depend on W sub m, with due account of the polarization effect of the medium.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 355-360
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  • 30
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    Spark calorimeter: An instrument for determining particle energy of cosmic radiation (1975)
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    Publication Date: 2011-08-16
    Description: In 1964 a spark calorimeter was installed at the NOR-Amberd Station (2000 m above sea level). The advantages of this calorimeter over the ionization calorimeter are illustrated.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 349-354
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  • 31
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    An instrument for the study of the composition of the electron component of cosmic rays (1975)
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    Publication Date: 2011-08-16
    Description: A telescope consisting of three spark chambers and two control scintillation counters has been designed and is used for investigating the composition of the cosmic ray electron component within the range of energies from 1.0 to 10.0 BeV by the EN assymetry method. The geometrical factor of the telescope is approximately 20 sq cm ster. Discharges are recorded in the chambers on a photo film. The telescope is oriented to the azimuth with an accuracy of + or - 3 deg.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 341-348
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  • 32
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    Gas threshold Cerenkov counters (1975)
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    Publication Date: 2011-08-16
    Description: The report describes two designs are reported of gas threshold Cerenkov counters for recording electrons of primary cosmic rays without recording protons. Also presented are design and technological measures which ensure maximum light collection of the Cerenkov radiation originating on the photocathode of the photomultiplier inside the radiator. The dependence of the reflection factor on the length of the light wave for different coatings is shown as well as for the throughput of the different optical materials employed. A range of methods for determining the efficiency of the counters during the recording of cosmic ray nucons and ways of increasing it further are given.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 327-332
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  • 33
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    Certain problems in the development and design of scintillation and Cerenkov counters (1975)
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    Publication Date: 2011-08-16
    Description: The feasibility is examined of increasing the effectiveness of the scintillation and Cerenkov counters through improving light collection of the recorded radiation on the photoelectric cathode of the photomultiplier. An example of how to select a detector of the directional plexiglas Cerenkov counter is given. Also presented are experimentally obtained amplitude distributions during the recording of cosmic ray muons. The necessity to obtain agreement between the characteristic spectrum of the photocathode of the photomultiplier and the spectrum of the recorded radiation is stressed.
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    Type: Cosmic Rays (NASA-TT-F-807); p 302-307
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    A system for multichannel recording and automatic reading of information (1975)
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    Publication Date: 2011-08-16
    Description: A system for the recording and processing of telescope data is considered for measurements of EW asymmetry. The information is recorded by 45 channels on a continuously moving 35-mm film. The dead time of the recorder is about 0.1 sec. A sorting electronic circuit is used to reduce the errors when the statistical time distribution of the pulses is recorded. The recorded information is read out by means of photoresistors. The phototransmitter signals are fed either to the mechanical recorder unit for preliminary processing, or to a logical circuit which controls the operation of the punching device. The punched tape is processed by an electronic computer.
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    Type: Cosmic Rays (NASA-TT-F-807); p 293-297
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    Description of an ionization calorimeter complemented with proportional counters (1975)
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    Publication Date: 2011-08-16
    Description: An ionization calorimeter is described with a system of proportional counters which are used to determine the charge of the particles incident to the calorimeter and to estimate the number of the secondary charged particles.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (; p 287-289
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  • 36
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    Large neutron counters for supermonitors (1975)
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    Publication Date: 2011-08-16
    Description: Large neutron counters designed for the neutron supermonitor with an area of about 20 sq m are reported. Statistical accuracy of the counters is 0.1% per 2 hours. Dimensions: length--2 m; diameter--150 mm; pressure--200 mm Hg. The counters are filled with BF3 gas containing over 80% of B-10.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (; p 279-281
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  • 37
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    The Helios A/B cosmic ray instrument /E 7/ (1975)
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    Publication Date: 2011-08-16
    Description: This paper describes the design and performance of a cosmic ray particle experiment for the Helios A/B space missions. This experiment had to be very lightweight, low power and electronically sophisticated in order to meet the spacecraft and scientific requirements, and very similar to those on the Pioneer 10 and 11 missions to Jupiter. Both sets of missions use several solid-state detector telescopes to measure protons from 100 KeV to 800 MeV per nucleon. Additionally, the Helios experiment includes a proportional counter to monitor the solar X-ray activity. The experiment has functioned quite well for 5 months in space, and large quantities of data are now being received.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Raumfahrtforschung; 19; Sept
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  • 38
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    The Solar Backscatter Ultraviolet and Total Ozone Mapping Spectrometer /SBUV/TOMS/ for Nimbus G (1975)
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    Publication Date: 2011-08-16
    Description: The SBUV/TOMS measures the atmospheric ozone vertical profile and the solar ultraviolet spectrum, and provides a total ozone map by means of a mechanical scan across the Nimbus track. While the SBUV/TOMS instrument has noteworthy design features such as a state-of-the-art double monochromator and fixed optical components on a nonmetallic structure, its most significant characteristic is an optimum system design based on technology proven on the BUV instrument.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 14; July-Aug
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  • 39
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    Plasma flow and fast particles in a hypervelocity accelerator - A color presentation (1975)
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    Publication Date: 2011-08-16
    Description: A new concept for particle acceleration for micrometeoroid simulation was developed at NASA Marshall Space Flight Center, using a high-density self-luminescent fast plasma flow to accelerate glass beads (with a diameter up to 1.0 mm) to velocities between 15-20 km/sec. After a short introduction to the operation of the hypervelocity range, the eight-converter-camera unit used for the photographs of the plasma flow and the accelerated particles is described. These photographs are obtained with an eight-segment reflecting pyramidal beam splitter. Wratten filters were mounted between the beam splitter and the converter tubes of the cameras. The photographs, which were recorded on black and white film, were used to make the matrices for the dye-color process, which produced the prints shown.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; Oct. 197
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  • 40
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    Theoretical study of lift-generated vortex wakes designed to avoid rollup (1975)
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    Publication Date: 2011-08-16
    Description: Two hypothetical vortex wakes are introduced and studied theoretically to explore whether the rollup of lift-generated vortex sheets can be suppressed. The circulation distribution across each wake is specified such that one rotates and the other translates as a unit due to their self-induced velocities. Several span loadings are constructed from these solutions and the resulting inviscid wake structure is computed for several span lengths behind the generating wing by use of the discrete vortex method wherein the vortex wake is represented by an array of vortices. The final distribution of vortices is then used to estimate the rolling moment on an encountering wing. It is found that, even though the initial specified motions are not sustained, substantial reductions in rolling moment are predicted for certain ranges of the ratio of the span of the generating wing to the following wing.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Apr. 197
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  • 41
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    CAMAC and NIM systems in the space program (1975)
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    Publication Date: 2011-08-16
    Description: The CAMAC and NIM instrumentation systems were developed originally to serve the needs of nuclear research institutions in Europe and North America. CAMAC and NIM are currently considered in several studies at the systems level conducted by NASA and ESRO groups. NIM and CAMAC studies for applications related to the space shuttle are discussed along with the advantages provided by aspects of modularization and standardization, a use of NIM and CAMAC equipment in connection with a group of astrophysics experiments, and questions of cost effectiveness.
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  • 42
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    Entopistic scintillators (1975)
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    Publication Date: 2011-08-16
    Description: Trajectories of cosmic rays through a balloon-borne experiment will be determined by pulse height analyzing the signals from each of the two or more phototubes coupled to each scintillator. Thin or tapered scintillators produce sufficiently strong gradients of phototube signal with respect to scintillation position that position uncertainties of about 1 cm can be achieved over 1-sq-m areas. Calculations and some test results for entopistic, or position determining, scintillators are presented.
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  • 43
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    Numerical solutions for supersonic corner flow (1975)
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    Publication Date: 2011-08-16
    Description: Analytical solutions for inviscid supersonic corner flows are virtually nonexistent due to the complexity of the interference geometry. In view of this, numerical solutions for swept-compressive and swept-expansive corner flows are obtained. The governing equations are written in strong conservation-law form and are solved iteratively in nonorthogonal conical coordinates by use of a second-order, shock-capturing, finite-difference technique. The computed wave structure and surface pressure distributions are compared with high Reynolds number experimental data and show very good agreement. The results clearly show that supersonic corner flow at reasonably high Reynolds numbers including the effect of sweep is dominated by the inviscid field.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics; 17; Feb. 197
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  • 44
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    Miniature probe for transonic flow direction measurements (1975)
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    Publication Date: 2011-08-16
    Description: A miniature probe is developed for measuring flow direction in one plane as well as stagnation pressure in the boundary layer and near wake of a transonic airfoil. The probe tip geometry and calibration curves are given, along with near wake survey data obtained for a supercritical airfoil. The advantages of the probe are ruggedness, ease of fabrication, ability to measure flow direction at a point, and insensitivity to out-of-plane velocity components.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal; 13; Feb. 197
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  • 45
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    Measured three-dimensional effects in transonic airfoil testing (1975)
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    Description: An investigation was conducted regarding the issue of deviation from two-dimensionality in flowfield studies of a supercritical airfoil. It was found that significant three-dimensional effects occur in transonic airfoil tests, even for an aspect ratio of four. This is especially true at the supercritical Mach numbers, for which lateral propagation of disturbances is effective.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Feb. 197
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  • 46
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    Aerodynamic characteristics of the planetary atmosphere experiments test entry probe (1975)
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    Publication Date: 2011-08-16
    Description: The aerodynamic characteristics of the Planetary Atmosphere Experiments Test entry probe were determined experimentally in ballistic range tests over a wide range of Mach and Reynolds numbers, and were compared with full-scale flight results. The ground facility data agreed with the full-scale data within 2 to 3% in drag coefficient, and within 5 to 10% in static stability, at the higher Mach numbers. Comparisons of the flight data with conventional wind-tunnel data indicated a significant disagreement in drag coefficient in the transonic speed range suggestive of important sting or wall interference effects. Variations in drag coefficient with Mach number were very small hypersonically, but variations with Reynolds number were of the order of 15% at a free-stream Mach number of 13 over the Reynolds number range from 10,000 to 1,000,000. Variations in the lift and static-stability curves with Mach number and Reynolds number were also defined.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 12; Jan. 197
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  • 47
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    On the computation of two- and three-dimensional steady transonic flows by relaxation methods (1975)
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    Publication Date: 2011-08-16
    Description: The paper is concerned with the application of the Murman and Cole (1971) relaxation scheme to steady, inviscid transonic flow problems in two and three dimensions. This scheme, which automatically accounts for weak shock waves, uses separate difference operators in elliptic and hyperbolic regions. The details of the scheme are described in terms of the original small disturbance formulation of Murman and Cole. In particular, Murman's recent (1973) introduction of fully conservative difference operators to obtain the correct shock jumps is examined. The extension to treating the exact isentropic equation is then covered with special attention given to Jameson's (to appear) rotated difference scheme for supersonic flow regions. The bulk of the discussion is related to two-dimensional procedures, and some comparisons with experiment are made, with emphasis on the effects of viscosity and wind-tunnel walls. Application of the Murman-Cole scheme is then discussed for small disturbances in three dimensions.
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  • 48
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    An efficient read-out system for multiwire proportional counter hodoscopes (1975)
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    Publication Date: 2011-08-16
    Description: An efficient scanning method for read-out of a multiwire proportional counter hodoscope is presented. This method which utilizes the grouping of wires in the hodoscope read-out system offers distinct advantages in speed and simplicity over systems employing long shift registers. Power consumption and cost can be minimized with this method because of slower clock speeds and a low parts count. This system has been constructed and used on a hodoscope for cosmic-ray trajectory measurements and a lower-power version has been designed for satellite applications.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 117; 1975
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  • 49
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    Holographic recording materials - A review (1975)
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    Publication Date: 2011-08-16
    Description: Holographic recording materials in current use are examined along with a few of their applications. Some experimental media are also studied. No effort is made to rank the commercial materials, since satisfactory results can be obtained with any of them. The discussion covers silver halide plates and films, photoresists, thermoplastics, photopolymers, dichromated gelatin, photochromic materials, electrooptical crystals, styryl free radical film, and TEP film. A convenient summation of some material properties is presented in tabular form.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 14; Sept
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    Multiple slot skin friction reduction (1975)
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    Publication Date: 2011-08-16
    Description: The paper investigates analytically the effect of multiple slot injection on skin friction for a representative fuselage shape (ogive-cylinder body) and evaluates the potential of slot injection as a drag reduction system in subsonic flow. Typical CTOL cruise flight conditions (Mach number equals 0.82 at altitudes of 11 km) were adopted for a fuselage 67.06 m in length and with maximum diameter of 7.32 m. The numerical method of Price and Harris (1972) was used to calculate the boundary-layer characteristics up to the first slot, while the finite-difference method of Beckwith and Bushnell (1971) was used to calculate the velocity profile downstream of one, three, five, or ten slots. An integral expression is proposed for characterizing skin friction reduction effectiveness, and it is seen that large reductions in viscous drag (50%) are available through slot injection. Skin friction reduction is improved by increasing the number of injection slots but at a diminishing rate.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 12; Sept
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  • 51
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    Mach and Reynolds number effects on turbulent skin friction reduction by injection (1975)
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    Publication Date: 2011-08-16
    Description: The investigation reported is concerned with questions regarding a possible Mach number influence on skin friction reduction caused by injection. The investigation shows that data considered by Danberg (1967) for the no-blowing skin friction coefficient are in error. Accurate profiles and local skin friction coefficient values are obtained when the influence of low Reynolds number amplification in the outer region of the boundary layer is included in a calculation method.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 12; Aug. 197
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  • 52
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    Cascade with subsonic leading-edge locus (1975)
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    Publication Date: 2011-08-16
    Description: The paper investigates a two-dimensional oscillating cascade with a subsonic leading edge locus in a supersonic flow. The blades are assumed to be of small thickness and camber, and are undergoing small amplitude-harmonic oscillations. The problem is reduced to the solution of a functional integral equation, and an expression is given for the kernel function.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Aug. 197
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  • 53
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    Composition analyzer for microparticles using a spark ion source (1975)
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    Publication Date: 2011-08-16
    Description: Iron microparticles were fired onto a capacitor-type microparticle detector which responded to an impact with a spark discharge. Ion currents were extracted from the spark and analyzed in a time-of-flight mass spectrometer. The mass spectra showed the elements of both detector and particle materials. The total extracted ion current was typically 10 A within a period of 100 nsec, indicating very efficient vaporization of the particle and ionization of the vapor. Potential applications include research on cosmic dust, atmospheric aerosols and cloud droplets, particles ejected by rocket or jet engines, by machining processes or by nuclear bomb explosions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 46; Nov. 197
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  • 54
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    The flow over a 'high' aspect ratio gothic wing at supersonic speeds (1975)
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    Publication Date: 2011-08-16
    Description: Results are presented of an experimental investigation on a nonconical wing which supports an attached shock wave over a region of the leading edge near the vertex and a detached shock elsewhere. The shock detachment point is determined from planform schlieren photographs of the flow field and discrepancies are shown to exist between this and the one calculated by applying the oblique shock equations normal to the leading edge. On a physical basis, it is argued that the shock detachment has to obey the two-dimensional law normal to the leading edges. From this, and from other measurements on conical wings, it is thought that the planform schlieren technique may not be particularly satisfactory for detecting shock detachment. Surface pressure distributions are presented and are explained in terms of the flow over related delta wings which are identified as a vertex delta wing and a local delta wing.
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  • 55
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    On the analytic structure of the Taylor-Maccoll conical-flow solution (1975)
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    Publication Date: 2011-08-16
    Description: The conical flow solution for axisymmetric supersonic flow past cones has been found to be virtually independent of the ratio of specific heats when normalized in a certain way. A simple rational approximation to this flow is derived. The important singularities and the limiting behavior of the solution are also discussed.
    Keywords: AERODYNAMICS
    Type: Zeitschrift fuer angewandte Mathematik und Physik; 26; July 25
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  • 56
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    Supersonic inlet contour interpolation (1975)
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    Publication Date: 2011-08-16
    Description: A method for designing supersonic inlet contours is described which consists in the interpolation of the contours of two known inlets designed for different Mach numbers, thereby determining the contours for a third inlet at an intermediate design Mach number. Several similar axisymmetric inlet contours were interpolated from known inlets with design Mach numbers ranging from 2.16 to 4.0 and with design Mach numbers differing by as much as 1.0. The flowfields were calculated according to Sorensen's (1965) computer program. Shockwave structure and pressure distribution characteristics are shown for the interpolated inlets. The validity of the interpolation is demonstrated by comparing the plots of the flowfield properties across the throat station of the interpolated inlet with the known inlets which were designed iteratively. It seems possible to write a computer program so that a matrix of known inlet contours can be interpolated.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 12; Sept
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  • 57
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    The radio astronomy experiment on Helios A and B /E 5c/ (1975)
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    Publication Date: 2011-08-16
    Description: The NASA Goddard Space Flight Center radio astronomy experiment on Helios, identified as Experiment 5c, has sixteen observing frequencies over the range of 26.5 to 3000 kHz. The antenna consists of two extendible 15-m booms, forming an electric dipole, two high-impedance preamplifiers located at the root of the booms, and the 16-channel radiometer. Important information about propagation conditions, such as absorption, scattering and refraction, are expected from observations of radio emission regions at distances between 1 and 0,3 AU.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Raumfahrtforschung; 19; Sept
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  • 58
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    The Rome-GSFC magnetic field experiment for Helios A and B /E 3/ (1975)
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    Publication Date: 2011-08-16
    Description: The Rome-GSFC magnetic field experiment utilizes a triaxial fluxgate (saturable inductor) magnetometer. The sensor unit is mounted on the end of a boom approximately four meters from the spacecraft spin axis. The three analog outputs of the magnetometer are converted into three 9 bit digital words. The experiment utilizes an automatic inflight range switch to select the optimum dynamic range out of 4 ranges. A nonmagnetic thermally oscillating actuator is used to reorient the sensor unit by 90 deg to determine all three axes zero levels. The accuracy should be approximately plus or minus 0.1 gamma. The vector measurements are made at equal intervals in time ranging from 16 per second down to 1 per second depending on the telemetry bit rate.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Raumfahrtforschung; 19; Sept
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    Optical-mechanical line-scan imaging process - Its information capacity and efficiency (1975)
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    Publication Date: 2011-08-16
    Description: Optical-mechanical line-scan techniques have been applied to earth satellite multispectral imaging systems. The capability of the imaging system is generally assessed by its information capacity. An approach based on information theory is developed to formulate the capacity of the line-scan process. Included are the effects of blurring of spatial detail, photosensor noise, aliasing, and quantization. The information efficiency is shown to be dependent on sampling rate, system frequency response shape, SNR, and quantization interval.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; Oct. 197
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  • 60
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    Diffraction analysis of Doppler signal characteristics for a cross-beam laser Doppler velocimeter (1975)
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    Publication Date: 2011-08-16
    Description: Based on scalar diffraction theory, single particle scattering characteristics for a cross-beam laser Doppler velocimeter (LDV) have been computed for different particle sizes under varied instrumentation configurations. The modulating component of the scattered signal has been shown to depend upon particle size, shape, and collecting aperture for a given probe volume fringe spacing. Experimental verifications of some of the predictions are presented, and some of the limitations using an LDV as a particle sizing instrument are discussed.
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    Type: Applied Optics; 14; Sept
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  • 61
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    Vacuum ultraviolet radiometry with hydrogen arcs. II - The high power arc as an absolute standard of spectral radiance from 124 nm to 360 nm (1975)
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    Publication Date: 2011-08-16
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; Sept
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  • 62
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    A coherent optical feedback system for optical information processing (1975)
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    Publication Date: 2011-08-16
    Description: A unique optical feedback system for coherent optical data processing is described. With the introduction of feedback, the well-known transfer function for feedback systems is obtained in two dimensions. Operational details of the optical feedback system are given. Experimental results of system applications in image restoration, contrast control and analog computation are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Physics; 8; Sept
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  • 63
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    Optimization of multimagnetometer systems on a spacecraft (1975)
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    Publication Date: 2011-08-16
    Description: The problem of optimizing the position of magnetometers along a boom of given length to yield a minimized total error is investigated. The discussion is limited to at most four magnetometers, which seems to be a practical limit due to weight, power, and financial considerations. The outlined error analysis is applied to some illustrative cases. The optimal magnetometer locations, for which the total error is minimum, are computed for given boom length, instrument errors, and very conservative magnetic field models characteristic for spacecraft with only a restricted or ineffective magnetic cleanliness program. It is shown that the error contribution by the magnetometer inaccuracy is increased as the number of magnetometers is increased, whereas the spacecraft field uncertainty is diminished by an appreciably larger amount.
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    Type: Journal of Geophysical Research; 80; Aug. 1
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  • 64
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    New high-temperature noble-metal thermocouple pairing (1975)
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    Description: A new thermocouple pairing was formed by combining thermocouple elements from two existing commercially available thermocouples to form a new combination (Ir-40 Rh/Pt-40 Rh) thermocouple. The output of this new pairing is nearly linear with temperature, and approximately equal to the output of one of the originating pairs (Ir-40 Rh/Ir), and more than double that of the other pair (Pt-40 Rh/Pt-20 Rh). This new pairing was evolved during a search for a noble-metal thermocouple combination which could operate above the temperature limit of a Pt-13 Rh/Pt thermocouple and have a higher oxidation resistance than an Ir-40 Rh/Ir thermocouple.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 46; Aug. 197
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  • 65
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    A balloon-borne ionization spectrometer with very large aperture for the detection of high energy cosmic rays (1975)
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    Publication Date: 2011-08-16
    Description: A balloon experiment which was used to determine the chemical composition of very high-energy cosmic rays up to and beyond 100 GeV/nucleon is described. The detector had a geometric factor of 1 sq m sr and a total weight on the balloon of 2100 kg. The apparatus consisted of an ionization spectrometer, spark chambers, and plastic scintillation and Cherenkov counters. It was calibrated at CERN up to 24 GeV/c protons and at DESY up to 7 GeV/c electrons. In October 1972 it was flown successfully on a stratospheric balloon.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 124; 1975
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  • 66
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    Absolute radiometric calibration of detectors between 200-600 A (1975)
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    Publication Date: 2011-08-16
    Description: A description is given of the experimental methods used in the calibration procedure, taking into account the source of radiant energy, the monochromator, the absolute standard detector, and the transfer standards. The experimental apparatus is discussed. A graph showing the effect of beam motion on the detected signal is presented and a block diagram of the calibration electronic system is provided.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; Apr. 197
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    Computation of three-dimensional, inviscid supersonic flows (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper sets forth in detail a method for the finite-difference computation of three-dimensional supersonic fields in an Eulerian mesh. First-, second-, and third-order finite difference schemes are examined. Attention is given to proper treatment of the impermeable and permeable boundaries encompassing the computational plane. Numerical results are presented for certain specific configurations: a conical wing-body combination, internal corner flow, a two-dimensional blunt body, an interfering shock problem, and three-dimensional inviscid supersonic flow past a shuttle-orbiter type vehicle.
    Keywords: AERODYNAMICS
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  • 68
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    Series solution for the planar asymmetric blunt-body problem (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Accurate semianalytic solutions to the inverse blunt-body problem have been obtained using a method of series expansion. Rational fractions are employed for series summation and analytic continuation. Angles of incidence up to 30 deg and Mach numbers as low as 2 have been considered. The maximum-entropy streamline will not wet the body surface in asymmetric flow. It may pass either above or below the stagnation streamline. Limit lines appear in the supersonic portion of the flow field, both in the shock layer and in its upstream analytic continuation.
    Keywords: AERODYNAMICS
    Type: Physics of Fluids; 18; Dec. 197
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  • 69
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    Hypersonic incipient separation on delta wing with trailing-edge flap (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper reviews the experimental data on the incipient separation characteristics of planar delta wings of 75 degree sharp leading edges, with full-span trailing edge flap deflected into the windward flow. The local Reynolds number range for these investigations covered laminar, transitional and turbulent conditions. It is shown that, while turbulent boundary layer data correlates with two dimensional results, in the laminar and transitional cases, there is a nearly parallel shift to higher flap angles for incipient separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Oct. 197
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  • 70
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    ATS-6 - Interferometer (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The ATS-6 interferometer provides precision, 3-axis attitude sensing capability. It incorporates a C-band receiver which measures the phase difference of continuous ground station signals received at paired antenna elements and converts this phase difference into digital data that is transmitted to the ground, and is also used as direct input to the onboard digital operations controller for conversion to attitude information. It uses 6 onboard horn antennas, placed in the earth viewing module, with three antennas arranged along each of two orthogonal baselines parallel to the satellite pitch and roll axes, one antenna used as a measurement reference on each baseline, and the remaining two horns, placed to provide phase measurements relative to the respective reference antenna.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
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  • 71
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    ATS-6 - The Geosynchronous Very High Resolution Radiometer (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Geosynchronous Very High Resolution Radiometer (GVHRR), flown on the three-axis stabilized geosynchronous satellite, Applications Technology Satellite-6 (ATS-6), collected meteorological data for two months during the summer of 1974. Several hundred images were successfully taken. Data collection terminated when the instrument chopper motor failed. The instrument, its supporting ground equipment, and the data collected in orbit are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
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  • 72
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    Forward marching procedure for separated boundary-layer flows (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A forward-marching procedure for separated boundary-layer flows which permits the rapid and accurate solution of flows of limited extent is presented. The streamwise convection of vorticity in the reversed flow region is neglected, and this approximation is incorporated into a previously developed (Carter, 1974) inverse boundary-layer procedure. The equations are solved by the Crank-Nicolson finite-difference scheme in which column iteration is carried out at each streamwise station. Instabilities encountered in the column iterations are removed by introducing timelike terms in the finite-difference equations. This provides both unconditional diagonal dominance and a column iterative scheme, found to be stable using the von Neumann stability analysis.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Aug. 197
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  • 73
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    The Apollo 15 and 16 X-ray fluorescence experiment (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An X-ray fluorescence spectrometer was flown aboard the Apollo 15 and 16 spacecrafts orbiting the moon. The X-ray instrument was used to produce a chemical map of that portion of the moon covered by the projected ground tracks and illuminated by the sun during the period of flight. The instrument includes three thin windowed proportional counters, two of which have selected X-ray filters. The field of view of the surface is determined by a collimator, while a detector on the opposite side of the spacecraft provides a continuous monitoring of the solar X-ray output. While the number of chemical elements determined was limited to Mg, Al, and Si, these proved to be very important diagnostic elements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Space Science Instrumentation; 1; Aug. 197
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  • 74
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    Radioactivity observed in the sodium iodide gamma-ray spectrometer returned on the Apollo 17 mission (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: In order to obtain information on radioactive background induced in the Apollo 15 and 16 gamma-ray spectrometers (7 cm x 7 cm NaI) by particle irradiation during spaceflight, and identical detector was flown and returned to earth on the Apollo 17 mission. The induced radioactivity was monitored both internally and externally from one and a half hours after splashdown. When used in conjunction with a computation scheme for estimating induced activation from calculated trapped proton and cosmic-ray fluences, these results show an important contribution resulting from both thermal and energetic neutrons produced in the heavy spacecraft by cosmic-ray interactions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Space Science Instrumentation; 1; Aug. 197
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  • 75
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    Errors in Hadamard spectroscopy or imaging caused by imperfect masks (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An analysis is given of the errors in Hadamard spectroscopy that are caused by transparent slits in the mask being systematically wider or narrower than they should be. It is shown that if the input spectrum consists of a single line, the distorted spectrum that is actually calculated consists of this line plus four small blips. When the transparent slits are too wide, these blips are of equal height and the same sign with one pair surrounding the line and another pair 5isplaced a certain distance from it. When the slits are too narrow, the displaced blips have the same amplitude, but are negative. The response to an arbitrary input spectrum is then determined from this. The same method of analysis may also be used to handle other types of errors.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 14; Nov. 197
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  • 76
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    Electrography and astronomical applications (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A review is presented of a conference on electrographic detectors in astronomy announced in IAA, issue 9, p. 1377, A75-23926. Different electrographic camera designs are described, and schematic diagrams of various image intensifiers (Lallemand, Kron, and Spectracon) are presented.
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  • 77
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    An experimental study of jet exhaust simulation (1975)
    In:  CASI
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    Publication Date: 2012-05-22
    Description: Afterbody drag predictions for jet aircraft are usually made experimentally with the jet exhaust flow simulated. The physical gas properties of the fluid used for the model jet exhaust can affect the accuracy of simulation of the airplane's jet exhaust plume. The effect of the accuracy of this simulation on afterbody drag was investigated by wind-tunnel tests with single engine model. In addition to unheated air as the exhaust gas, the decomposition products of three different concentrations of hydrogen peroxide were utilized. The air jet simulation consistently resulted in higher boattail drag than hydrogen peroxide simulation. The differences in drag for the various exhaust gases are attributed to different plume shapes and entrainment properties of the gases. The largest differences in drag due to exhaust gas properties were obtained for the combination of high transonic Mach numbers and high boattail angles. For these conditions, the current data indicate that the use of air to simulate a nonafterburning turbojet exhaust can result in an increase in afterbody amounting to 20 percent of the nonafterburning turbojet value.
    Keywords: AERODYNAMICS
    Type: AGARD Airframe(Propulsion Interference; 11 p
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  • 78
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    Reynolds number effects on boattail drag of exhaust nozzles from wind tunnel and flight tests (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: A family of nacelle mounted high angle boattail nozzles was tested to investigate Reynolds number effects on drag. The nozzles were flown on a modified F-106B and mounted on scale models of an F-106 in a wind tunnel. A 19- to 1-range of Reynolds number was covered as a result of the large size differences between models and by flying over a range of altitude. In flight the nozzles were mounted behind J-85 turbojet engines. Jet boundary simulators and a powered turbojet engine simulator were used on the wind tunnel models. Data were taken at Mach numbers of 0.6 and 0.9. Boattail drag was found to be affected by Reynolds number. The effect is a complex relationship dependent upon boundary layer thickness and nozzle boattail shape. As Reynolds number was increased from the lowest values obtained with scale models, boattail drag first increased to a maximum at the lowest flight Reynolds number and then decreased.
    Keywords: AERODYNAMICS
    Type: AGARD Airframe(Propulsion Interference; 15 p
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  • 79
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    An aerodynamic load criterion for airships (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A simple aerodynamic bending moment envelope is derived for conventionally shaped airships. This criterion is intended to be used, much like the Naval Architect's standard wave, for preliminary estimates of longitudinal strength requirements. It should be useful in tradeoff studies between speed, fineness ratio, block coefficient, structure weight, and other such general parameters of airship design.
    Keywords: AERODYNAMICS
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 169-176
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  • 80
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    Overview of external Nacelle drag and interference drag (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A historical view of multi-jet engine installations is given that emphasizes integration of the powerplant and the airframe in aircraft design for improved reduction in external nacelle drag and interference drag characteristics.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 235-244
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  • 81
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    Computational aspects of the prediction of multidimensional transonic flows in turbomachinery (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The analytical prediction and description of transonic flow in turbomachinery is complicated by three fundamental effects: (1) the fluid equations describing the transonic regime are inherently nonlinear, (2) shock waves may be present in the flow, and (3) turbomachine blading is geometrically complex, possessing large amounts of curvature, stagger, and twist. A three-dimensional computation procedure for the study of transonic turbomachine fluid mechanics is described. The fluid differential equations and corresponding difference operators are presented, the boundary conditions for complex blade shapes are described, and the computational implementation and mapping procedures are developed. Illustrative results of a typical unthrottled transonic rotor are also presented.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 567-585
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  • 82
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    Simulation of turbulent transonic separated flow over an airfoil (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A code developed for simulating high Reynolds number transonic flow fields of arbitrary configuration is described. This code, in conjunction with laboratory experiments, is used to devise and test turbulence transport models which may be suitable in the prediction of such flow fields, with particular emphasis on regions of flow separation. The solutions describe the flow field, including both the shock-induced and trailing-edge separation regions, in sufficient detail to provide the profile and friction drag.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 419-436
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  • 83
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    On the calculation of supersonic, separating, and reattaching flows (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A method is developed for solving the laminar and turbulent compressible boundary-layer equations for separating and reattaching flows. Results of this method are compared with experimental data for two laminar and three turbulent boundary-layer, shock-wave interactions. Several Navier-Stokes solutions were obtained for each of the laminar boundary-layer, shock-wave interactions considered. Comparison of these solutions indicates a first-order sensitivity in C sub f to the computational mesh selected in both the viscous and inviscid portions of the flow.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 151-175
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  • 84
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    Internal and external axial corner flows (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The inviscid, internal, and external axial corner flows generated by two intersecting wedges traveling supersonically are obtained by use of a second-order shock-capturing, finite-difference approach. The governing equations are solved iteratively in conical coordinates to yield the complicated wave structure of the internal corner and the simple peripheral shock of the external corner. The numerical results for the internal flows compare favorably with existing experimental data.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 643-658
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  • 85
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    Numerical computation of viscous flows on the lee side of blunt shapes flying at supersonic speeds (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A numerical method for solving the parabolic approximation to the steady-state compressible Navier-Stokes equations is examined. The approximation neglects only the streamwise gradients of shear stress. An implicit finite difference method is used which advances the solution downstream from an initial data surface and determines the complete viscous-inviscid flow between the body and bow shock wave. It is necessary that the inviscid portion of the flow field be supersonic. Crossflow separation is determined as part of the solution. The method is applied to a 15 deg sphere-cone at 15 deg angle of attack, and the results are compared with an inviscid method-of-characteristics calculation.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 531-542
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  • 86
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    Long fluid filled bags suspended by line forces (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A previous analysis of fluid filled storage bags is extended to the case of a long fluid filled cylindrical membrane supported by uniform line loads. Cross-sectional shape, stiffness of the support system and stress resultants in the membrane are determined. The application of the numerical results to problems arising in the design of nonrigid airships is discussed.
    Keywords: AERODYNAMICS
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 199-208
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  • 87
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    The planar dynamics of airships (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The forces and moments acting upon a LTA vehicle are considered in order to develop parameters describing planar motion. Similar expressions for HTA vehicles will be given to emphasize the greater complexity of aerodynamic effects when buoyancy effects cannot be neglected. A brief summary is also given of the use of virtual mass coefficients to calculate loads on airships.
    Keywords: AERODYNAMICS
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 177-186
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  • 88
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    General overview of drag (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The state-of-the-art on aerodynamic drag reduction is briefly reviewed. The various elements making up the total drag of an aircraft include fuselage, wing, nacelles, trim, interference, tail, and cooling drag.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 11-37
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  • 89
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    Drag of the complete configuration aerodynamic considerations, 2 (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A number of drag items are related to the performance of a complete aircraft configuration. First, the effect of fuselage camber, wing and nacelle incidence are discussed from a viewpoint of design decision making. Second, the effect of overall cruise drag on the design gross and empty weight of the airplane is discussed. Examples show that cruise drag can have a very important influence on total airplane weight. Third, the effects of usable cruise lift-to-drag ratio and wing loading are shown to be important. Finally several research needs relating to design of the complete configuration are reviewed.
    Keywords: AERODYNAMICS
    Type: Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 337-351
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  • 90
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    Trim Drag in the Light of Munk's Stagger Theorem (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Munk's stagger theorem holds that the induced drag of a multiplane is independent of the streamwise position (the stagger) of its lifting elements so long as the gap/span ratios and the element/element lift ratios are specified. In particular, a monoplane-tailplane or a monoplane-foreplane (canard)arrangement can be regarded as a biplane of zero gap and the trim drag due to tailplane download or foreplane upload can be readily calculated. The trim drag penalty is the same for both configurations. Relations are given for trim drag estimates for various practical arrangements.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 319-329
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  • 91
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    Wing Tip Vortex Drag (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Optimization of L/D through minimizing induced drag through a detailed flow study together with force, pressure and vorticity measurements is considered. Flow visualization with neutral helium bubbles provides an excellent means of observing the effects of configuration changes.
    Keywords: AERODYNAMICS
    Type: Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 215-233
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  • 92
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    Preservation of wing leading edge suction at the plane of symmetry as a factor in wing-fuselage design (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Most fuselage geometries cover a portion of the wing leading edge near the plane of symmetry, and it seems reasonable to expect that a large fraction of the leading edge suction which would be developed by the covered wing at high angles of attack is not developed on the fuselage. This is one of the reasons that the Oswald span efficiency factor for the wing body combination fails to approach the value predicted by lifting line theory for the isolated wing. Some traditional and recent literature on wing-body interference is discussed and high Reynolds number data on wing-body-nacelle drag are reviewed. An exposed central leading edge geometry has been developed for a sailplane configuration. Low Reynolds number tests have not validated the design concept.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 107-115
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  • 93
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    Prospects and time tables for analytical estimation of the drag of complete aircraft configuration (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Analytical drag methods and wind tunnel evaluation of aircraft design features are used to identify excessive drag of general aviation aircraft with reciprocating engines.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 39-41
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  • 94
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    Summary of drag clean-up tests in NASA Langley full-scale tunnel (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: This summary of drag results presents tabulations on fighter aircraft and light twin general aviation aircraft wind tunnel tests. The figures show that the friction drag for light twins is larger than that for the fighters because of the greater wetted area and the smaller wing area used for reference. Full scale tunnel tests developed the following design features contributing to excessive drag: cooling flow system, engine exhaust stacks, landing gears, control surface gaps, and wing irregularities and leakages.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 43-60
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  • 95
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    An investigation of several numerical procedures for time-asymptotic compressible Navier-Stokes solutions (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The status of an investigation of four numerical techniques for the time-dependent compressible Navier-Stokes equations is presented. Results for free shear layer calculations in the Reynolds number range from 1000 to 81000 indicate that a sequential alternating-direction implicit (ADI) finite-difference procedure requires longer computing times to reach steady state than a low-storage hopscotch finite-difference procedure. A finite-element method with cubic approximating functions was found to require excessive computer storage and computation times. A fourth method, an alternating-direction cubic spline technique which is still being tested, is also described.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 437-468
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  • 96
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    Subgrid or Reynolds stress-modeling for three-dimensional turbulence computations (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A review is given of recent advances in two distinct computational methods for evaluating turbulence fields, namely, statistical Reynolds stress modeling and turbulence simulation, where large eddies are followed in time. It is shown that evaluation of the mean Reynolds stresses, rather than use of a scalar eddy viscosity, permits an explanation of streamline curvature effects found in several experiments. Turbulence simulation, with a new volume averaging technique and third-order accurate finite-difference computing is shown to predict the decay of isotropic turbulence in incompressible flow with rather modest computer storage requirements, even at Reynolds numbers of aerodynamic interest.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 317-339
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  • 97
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    Solutions for incompressible separated boundary layers including viscous-inviscid interaction (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Numerical solutions are presented for the laminar and turbulent boundary-layer equations for incompressible flows with separation and reattachment. The separation angularity is avoided by using an inverse technique in which the displacement thickness is prescribed and the pressure is deduced from the resulting solution. The turbulent results appear qualitatively correct despite the use of a two-layer eddy-viscosity model which is generally assumed appropriate only for mild-pressure-gradient flows. A new viscous-inviscid interaction technique is presented in which the inviscid flow is solved inversely by prescribing the pressure from the boundary-layer solution and deducing the new displacement thickness from the solution of a Cauchy integral. Calculations are presented using this interaction procedure for a laminar flow in which separation and reattachment occur on a solid surface.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 125-150
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  • 98
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    A comparison of a shock-capturing technique with experimental data for three-dimensional internal flows (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Shock-capturing solutions for an axisymmetric supersonic inlet at small angles of attack are obtained. Good overall agreement between the shock-capturing solutions and experimental data is shown except in regions of strong viscous effects or boundary-layer removal. Although the results indicate a strong potential for the use of shock-capturing or finite-difference solutions for internal flows, improvement in the ability to handle the reflection of strong shockwaves having downstream Mach numbers near 1 is needed.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 623-642
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  • 99
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    Calculation of three-dimensional compressible laminar and turbulent boundary layers. Calculation of three-dimensional compressible boundary layers on arbitrary wings (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A very general method for calculating compressible three-dimensional laminar and turbulent boundary layers on arbitrary wings is described. The method utilizes a nonorthogonal coordinate system for the boundary-layer calculations and includes a geometry package that represents the wing analytically. In the calculations all the geometric parameters of the coordinate system are accounted for. The Reynolds shear-stress terms are modeled by an eddy-viscosity formulation developed by Cebeci. The governing equations are solved by a very efficient two-point finite-difference method used earlier by Keller and Cebeci for two-dimensional flows and later by Cebeci for three-dimensional flows.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 41-76
    Format: application/pdf
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    Calculation of supersonic three-dimensional free-mixing flows using the parabolic-elliptic Navier-Stokes equations (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A numerical method is presented which is valid for integration of the parabolic-elliptic Navier-Stokes equations. The solution procedure is applied to the three-dimensional supersonic flow of a jet issuing into a supersonic free stream. Difficulties associated with the imposition of free-stream boundary conditions are noted, and a coordinate transformation, which maps the point at infinity onto a finite value, is introduced to alleviate these difficulties. Results are presented for calculations of a square jet and varying-aspect-ratio rectangular jets. The solution behavior varies from axisymmetry for the square jet to nearly two-dimensional for the high-aspect-ratio rectangle, although the computation always calculates the flow as though it were truly three-dimensional.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 543-565
    Format: application/pdf
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