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  • Other Sources  (4)
  • 1995-1999  (3)
  • 1975-1979  (1)
  • 1996  (3)
  • 1979  (1)
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  • 1995-1999  (3)
  • 1975-1979  (1)
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  • 1
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    Cortical bone growth and maturational changes in dwarf rats induced by recombinant human growth hormone (1996)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The growth hormone (GH)-deficient dwarf rat was used to investigate recombinant human (rh) GH-induced bone formation and to determine whether rhGH facilitates simultaneous increases in bone formation and bone maturation during rapid growth. Twenty dwarf rats, 37 days of age, were randomly assigned to dwarf plus rhGH (GH; n = 10) and dwarf plus vehicle (n = 10) groups. The GH group received 1.25 mg rhGH/kg body wt two times daily for 14 days. Biochemical, morphological, and X-ray diffraction measurements were performed on the femur middiaphysis. rhGH stimulated new bone growth in the GH group, as demonstrated by significant increases (P 〈 0.05) in longitudinal bone length (6%), middiaphyseal cross-sectional area (20%), and the amount of newly accreted bone collagen (28%) in the total pool of middiaphyseal bone collagen. Cortical bone density, mean hydroxyapatite crystal size, and the calcium and collagen contents (microgram/mm3) were significantly smaller in the GH group (P 〈 0.05). Our findings suggest that the processes regulating new collagen accretion, bone collagen maturation, and mean hydroxyapatite crystal size may be independently regulated during rapid growth.
    Keywords: Aerospace Medicine
    Type: The American journal of physiology (ISSN 0002-9513); Volume 270; 1 Pt 1; E51-9
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Energy Spectrum in the Dissipation Range of Fluid Turbulence (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High resolution, direct numerical simulations of the three-dimensional incompressible Navier-Stokes equations are carried out to study the energy spectrum in the dissipation range. An energy spectrum of the form A(k/k( sub d))(sup alpha) exp[- betak/k(sub d) is confirmed. The possible values of the parameters alpha and beta, as well as their dependence on Revnolds numbers and length scales, are investigated, showing good agreement with recent theoretical predictions. A "bottleneck'-type effect is reported at k/k(sub d) approximately 4, exhibiting a possible transition from near-dissipation to far- dissipation.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-CR-198344 , NAS1.26:198344 , ICASE 96-42
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Definition of 1992 Technology Aircraft Noise Levels and the Methodology for Assessing Airplane Noise Impact of Component Noise Reduction Concepts (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the methodology for assessing the impact of component noise reduction on total airplane system noise. The methodology is intended to be applied to the results of individual study elements of the NASA-Advanced Subsonic Technology (AST) Noise Reduction Program, which will address the development of noise reduction concepts for specific components. Program progress will be assessed in terms of noise reduction achieved, relative to baseline levels representative of 1992 technology airplane/engine design and performance. In this report, the 1992 technology reference levels are defined for assessment models based on four airplane sizes - an average business jet and three commercial transports: a small twin, a medium sized twin, and a large quad. Study results indicate that component changes defined as program final goals for nacelle treatment and engine/airframe source noise reduction would achieve from 6-7 EPNdB reduction of total airplane noise at FAR 36 Stage 3 noise certification conditions for all of the airplane noise assessment models.
    Keywords: Acoustics
    Type: NASA-CR-198298 , NAS 1.26:198298
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Orbital transfer vehicle advanced expander cycle engine point design study (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed computer model of the expander cycle engine system steady-state operation was developed. Payload performance data for the expander cycle engine for 100K pounds and 65K pounds Space Shuttle missions were examined to establish peak payload thrusts. It was found that peak payload for the 100K pound gross weight single engine case occurred at nearly 15,000 pounds thrust for both engine mixture ratios of 6:1 and 7:1. Peak payload at engine mixture ratio of 6:1 was 4 percent greater than at 7:1 mixture ratio. The two engine configuration peak paYloads occurred at engine thrust below 7,500 pounds (extrapolated) and were lower than single engine payloads. For the 65K pound gross weight mission, peak payloads for the single engine configuration occurred at nearly 10,000 pounds for both mixture ratios. Mixture ratio of 7:1 payloads were 5 percent lower than 6:1 payloads. Two engine configuration payloads occurred at engine thrusts considerably below 10K pounds.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161318 , ASR79-109 , BMPR-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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