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  • 1
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    Multigrid calculation of three-dimensional viscous cascade flows (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 9; 4; p. 605-614.
    Format: text
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  • 2
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    High-performance-vehicle technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion needs of high performance military aircraft are discussed. Inlet performance, nozzle performance and cooling, and afterburner performance are covered. It is concluded that nonaxisymmetric nozzles provide cleaner external lines and enhanced maneuverability, but the internal flows are more complex. Swirl afterburners show promise for enhanced performance in the high altitude, low Mach number region.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 445-462
    Format: text
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  • 3
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    A schlieren technique for measuring jet penetration into a supersonic stream (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Schlieren optical method for measuring He jet penetration into supersonic flow
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ; 17 (
    Format: text
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  • 4
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    Swirling base injection for supersonic combustion ramjets. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Experimental evaluation of the swirling base injection proposed by Swithenbank and Chigier (1969) for application in supersonic combustion ramjets or scramjets. This concept of accelerated mixing in supersonic streams through swirl was tested, but the results indicate that swirl does not produce any enhancement of mixing.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 10; Sept
    Format: text
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  • 5
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    Behavior of large aluminum particles in composite propellants (1965)
    In:  Other Sources
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    Publication Date: 2011-08-10
    Description: Large aluminum particle behavior in composite propellant combustion
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 6
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    Spectrographic measurements of composite propellant flame zone structure (1965)
    In:  Other Sources
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    Publication Date: 2011-08-10
    Description: Spectrographic measurements of composite solid propellant flame zone structure
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 7
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    Large Eddy Simulation in the Computation of Jet Noise (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Noise can be predicted by solving Full (time-dependent) Compressible Navier-Stokes Equation (FCNSE) with computational domain. The fluctuating near field of the jet produces propagating pressure waves that produce far-field sound. The fluctuating flow field as a function of time is needed in order to calculate sound from first principles. Noise can be predicted by solving the full, time-dependent, compressible Navier-Stokes equations with the computational domain extended to far field - but this is not feasible as indicated above. At high Reynolds number of technological interest turbulence has large range of scales. Direct numerical simulations (DNS) can not capture the small scales of turbulence. The large scales are more efficient than the small scales in radiating sound. The emphasize is thus on calculating sound radiated by large scales.
    Keywords: Acoustics
    Type: First NASA/Industry High Speed Research Program Nozzle Symposium; 25-1 - 25-7; NASA/CP-1999-209423
    Format: application/pdf
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  • 8
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    Overview of Aerothermodynamic Loads Definition Study (1985)
    In:  CASI
    Details
    Publication Date: 2014-08-30
    Description: The Aerothermodynamic Loads Definition were studied to develop methods to more accurately predict the operating environment in the space shuttle main engine (SSME) components. Development of steady and time-dependent, three-dimensional viscous computer codes and experimental verification and engine diagnostic testing are considered. The steady, nonsteady, and transient operating loads are defined to accurately predict powerhead life. Improvements in the structural durability of the SSME turbine drive systems depends on the knowledge of the aerothermodynamic behavior of the flow through the preburner, turbine, turnaround duct, gas manifold, and injector post regions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 3-5
    Format: text
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  • 9
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    Investigation of mixing in a turbofan exhaust duct. II Computer code application and verification (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A three-dimensional analysis of turbofan forced mixer nozzle aerodynamics demonstrates that the complex flow structure is dominated by geometrically induced secondary flow rather than by turbulence. The test apparatus consisted of a fixed upstream model section and a rotating shroud. The Mach number of the fan and core streams at the mixing plane (lobe exit) was 0.45, the bypass ratio was about 4, and the Reynolds number based on the shroud radius was 1,100,000. The three velocity components near the exit plane of the lobes were measured using flow angularity probes to provide information about the mixer inflow conditions for turbulent computations. The validity of a previous computer code was demonstrated in a comparison of the nozzle exit temperature data with the computed temperature distributions. The mechanism most responsible for the generation of secondary flow within the lobes is due to the turning of the fan and core streams in opposite radial directions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA Journal (ISSN 0001-1452); 22; 518-525
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  • 10
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    Particulate damping in solid propellant combustion instability. (1967)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Aluminum powder damping of HF instability in solid propellant combustion in vortex burner
    Keywords: THERMODYNAMICS AND COMBUSTION
    Format: text
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