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  • Other Sources  (31)
  • Lunar and Planetary Science and Exploration  (11)
  • AERODYNAMICS  (10)
  • Optics
  • Spacecraft Propulsion and Power
  • 2005-2009  (18)
  • 1990-1994  (13)
  • 1
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    Navigation for Low-Cost Missions to Small Solar-System Bodies (1994)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Keywords: Lunar and Planetary Science and Exploration
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Navigation for Low-Cost Missions to Small Solar-System Bodies (1994)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: A variety of low-cost space missions planned by NASA for flight in the late 1990's and early 2000's will involve rendevous with, and orbits about, small solar-system bodies such as asteroids and comets.
    Keywords: Lunar and Planetary Science and Exploration
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Testing the Reliability of Cluster Mass Indicators with a Systematics Limited Dataset (2009)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: We present the mass X-ray observable scaling relationships for clusters of galaxies using the XMM-Newton cluster catalog of Snowden et al. Our results are roughly consistent with previous observational and theoretical work, with one major exception. We find 2-3 times the scatter around the best fit mass scaling relationships as expected from cluster simulations or seen in other observational studies. We suggest that this is a consequence of using hydrostatic mass, as opposed to virial mass, and is due to the explicit dependence of the hydrostatic mass on the gradients of the temperature and gas density profiles. We find a larger range of slope in the cluster temperature profiles at radii 500 than previous observational studies. Additionally, we find only a weak dependence of the gas mass fraction on cluster mass, consistent with a constant. Our average gas mass fraction results also argue for a closer study of the systematic errors due to instrumental calibration and modeling method variations between analyses. We suggest that a more careful study of the differences between various observational results and with cluster simulations is needed to understand sources of bias and scatter in cosmological studies of galaxy clusters.
    Keywords: Lunar and Planetary Science and Exploration
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Some Considerations for Precision Metrology of Thin X-Ray Mirrors (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: Determination of the shape of very thin x-ray mirrors employed in spaced-based telescopes continues to be challenging. The mirrors shapes are not readily deduced to the required accuracy because the mount induced distortions are often larger than the uncertainty tolerable for the mission metrology. In addition to static deformations, dynamic and thermal considerations are exacerbated for this class of mirrors. We report on the performance of one temporary mounting scheme for the thin glass mirrors for the Constellation-X mission and prospects for deducing their undistorted shapes.
    Keywords: Optics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    NASA Ames Fluid Mechanics Laboratory research briefs (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Ames Fluid Mechanics Laboratory research program is presented in a series of research briefs. Nineteen projects covering aeronautical fluid mechanics and related areas are discussed and augmented with the publication and presentation output of the Branch for the period 1990-1993.
    Keywords: AERODYNAMICS
    Type: NASA-TM-108818 , A-94073 , NAS 1.15:108818
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  • 6
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    Experimental investigation of turbulent flow through a circular-to-rectangular transition duct (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Steady, incompressible, turbulent, swirl-free flow through a circular-to-rectangular transition duck was studied experimentally. The cross-sectional area remains the same at the exit as at the inlet, but varies through the transition section to a maximum value approximately 15 percent above the inlet value. The cross-sectional geometry everywhere along the duct is defined by the equation of a superellipse. Mean and turbulence data were accumulated utilizing pressure and hot-wire instrumentation at five stations along the test section. Data are presented for operating bulk Reynolds numbers of 88,000 and 390,000. Measured quantities include total and static pressure, the three components of the mean velocity vector, and the six components of the Reynolds stress tensor. In addition to the transition duct measurements, a hot-wire technique which relies on the sequential use of single rotatable normal and slant-wire probes was proposed. The technique is applicable for measurement of the total mean velocity vector and the complete Reynolds stress tensor when the primary flow is arbitrarily skewed relative to a plane which lies normal to the probe axis of rotation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-105210 , E-6522 , NAS 1.15:105210
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A study of transonic aerodynamic analysis methods for use with a hypersonic aircraft synthesis code (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A means of performing routine transonic lift, drag, and moment analyses on hypersonic all-body and wing-body configurations were studied. The analysis method is to be used in conjunction with the Hypersonic Vehicle Optimization Code (HAVOC). A review of existing techniques is presented, after which three methods, chosen to represent a spectrum of capabilities, are tested and the results are compared with experimental data. The three methods consist of a wave drag code, a full potential code, and a Navier-Stokes code. The wave drag code, representing the empirical approach, has very fast CPU times, but very limited and sporadic results. The full potential code provides results which compare favorably to the wind tunnel data, but with a dramatic increase in computational time. Even more extreme is the Navier-Stokes code, which provides the most favorable and complete results, but with a very large turnaround time. The full potential code, TRANAIR, is used for additional analyses, because of the superior results it can provide over empirical and semi-empirical methods, and because of its automated grid generation. TRANAIR analyses include an all body hypersonic cruise configuration and an oblique flying wing supersonic transport.
    Keywords: AERODYNAMICS
    Type: NASA-CR-189854 , NAS 1.26:189854
    Format: application/pdf
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  • 8
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    Surface and flow field measurements in a symmetric crossing shock wave/turbulent boundary layer flow (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results of an experimental investigation of a symmetric crossing shock/turbulent boundary layer interaction are presented for a Mach number of 3.44 and deflections angles of 2, 6, 8 and 9 deg. The interaction strengths vary from weak to strong enough to cause a large region of separated flow. Measured quantities include surface static pressure and flowfield Pitot pressures. Pitot profiles in the plane of symmetry through the interaction region are shown for various deflection angles. Oil flow visualization and the results of a trace gas streamline tracking technique are also presented.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2634
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The feasibility of using a contoured honeycomb model to generate a thick boundary layer in high-speed, compressible flow was investigated. The contour of the honeycomb was tailored to selectively remove momentum in a minimum of streamwise distance to create an artificially thickened turbulent boundary layer. Three wind tunnel experiments were conducted to verify the concept. Results indicate that this technique is a viable concept, especially for high-speed inlet testing applications. In addition, the compactness of the honeycomb boundary layer simulator allows relatively easy integration into existing wind tunnel model hardware.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3142 , E-5660 , NAS 1.60:3142
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Ethylene Trace-gas Techniques for High-speed Flows (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Three applications of the ethylene trace-gas technique to high-speed flows are described: flow-field tracking, air-to-air mixing, and bleed mass-flow measurement. The technique involves injecting a non-reacting gas (ethylene) into the flow field and measuring the concentration distribution in a downstream plane. From the distributions, information about flow development, mixing, and mass-flow rates can be dtermined. The trace-gas apparatus and special considerations for use in high-speed flow are discussed. A description of each application, including uncertainty estimates is followed by a demonstrative example.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106491 , AIAA PAPER 94-0733 , E-8478 , NAS 1.15:106491 , Aerospace Meeting and Exhibit; Jan 10, 1994 - Jan 13, 1994; Reno, NV; United States
    Format: application/pdf
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