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  • AERODYNAMICS  (2)
  • CHEMISTRY AND MATERIALS (GENERAL)  (2)
  • 2000-2004
  • 1975-1979  (4)
  • 1978  (4)
  • 1
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    Stability of chromium (III) sulfate in atmospheres containing oxygen and sulfur (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The stability of chromium sulfate in the temperature range from 880 K to 1040 K was determined by employing a dynamic gas-solid equilibration technique. The solid chromium sulfate was equilibrated in a gas stream of controlled SO3 potential. Thermogravimetric and differential thermal analyses were used to follow the decomposition of chromium sulfate. X-ray diffraction analysis indicated that the decomposition product was crystalline Cr2O3 and that the mutual solubility between Cr2(SO4)3 and Cr2O3 was negligible. Over the temperature range investigated, the decomposition pressure were significantly high so that chromium sulfate is not expected to form on commercial alloys containing chromium when exposed to gaseous environments containing oxygen and sulfur (such as those encountered in coal gasification).
    Keywords: CHEMISTRY AND MATERIALS (GENERAL)
    Type: NASA-TM-78504 , A-7508
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Side-force alleviation on slender, pointed forebodies at high angles of attack (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new device was proposed for alleviating high angle-of-attack side force on slender, pointed forebodies. A symmetrical pair of separation strips in the form of helical ridges are applied to the forebody to disrupt the primary lee-side vortices and thereby avoid the instability that produces vortex asymmetry. Preliminary wind tunnel tests at Mach 0.3 and Reynolds no. 5,250,000 on a variety of forebody configurations and on a wing-body combination at angles of attack up to 56 degrees, demonstrated the effectiveness of the device.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145361
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Determination of volume fraction in multiphase systems using incomplete pole figures (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The determination of the volume fraction of a second phase in a multiphase sample by X-ray diffraction becomes more difficult if the diffracting planes have a preferred orientation. Lopata and Kula have described a method of treating this problem using complete pole figures for each of the phases. With some samples, it is not always possible or convenient to obtain data over the full hemisphere. Equations and an example are given which require X-ray data over a limited range of approximately 0 to 75 deg. This can be obtained by reflection without a specially cut sample or transmission data. A series of Legendre polynomials are fitted to data collected while spinning the sample about its normal. An extrapolation is made possible by introducing two conditions on the end points which must be satisfied if the extrapolation functions are to be valid.
    Keywords: CHEMISTRY AND MATERIALS (GENERAL)
    Type: Metallurgical Transactions A - Physical Metallurgy and Materials Science; 9A; Oct. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Wind tunnel tests on a tail-less swept wing span-distributed cargo aircraft configuration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The configuration consisted of a 30 deg -swept, untapered, untwisted wing utilizing a low-moment cambered airfoil of 20 percent streamwise thickness designed for low wave drag at M = 0.6, C sub L = 0.4. The tests covered a range of Mach numbers 0.3 to 0.725 and chord Reynolds number 1,100,000 to 2,040,000, angles of attack up to model buffet and sideslip angles + or - 4 deg. Configuration build up, wing pod filleting, airfoil modification and trailing edge control deflection effects were briefly investigated. Three wing tip vertical tail designs were also tested. Wing body filleting and a simple airfoil modification both produced increments to maximum lift/drag ratio. Addition of pods eliminated pitch instability of the basic wing. While the magnitude of these benefits probably was Reynolds number sensitive, they underline the potential for improving the aerodynamics of the present configuration. The cruise parameter (product of Mach number and lift/drag ratio) attained a maximum close to the airfoil design point. The configuration was found to be positively stable with normal control effectiveness about all three axes in the Mach number and C sub L range of interest.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78767
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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