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  • 1
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    Preliminary calibration of a generic scramjet combustor (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of a preliminary investigation of the combustion of hydrogen fuel at hypersonic flow conditions are provided. The tests were performed in a generic, constant-area combustor model with test gas supplied by a free-piston-driven reflected-shock tunnel. Static pressure measurements along the combustor wall indicated that burning did occur for combustor inlet conditions of P(static) approximately equal to 19kPa, T(static) approximately equal to 1080 K, and U approximately equal to 3630 m/s with a fuel equivalence ratio approximately equal to 0.9. These inlet conditions were obtained by operating the tunnel with stagnation enthalpy approximately equal to 8.1 MJ/kg, stagnation pressure approximately equal to 52 MPa, and a contoured nozzle with a nominal exit Mach number of 5.5.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-187539 , NAS 1.26:187539 , ICASE-16 , AD-A234873
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Study of compressible flow through a rectangular-to-semiannular transition duct (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Detailed flow field measurements are presented for compressible flow through a diffusing rectangular-to-semiannular transition duct. Comparisons are made with published computational results for flow through the duct. Three-dimensional velocity vectors and total pressures were measured at the exit plane of the diffuser model. The inlet flow was also measured. These measurements are made using calibrated five-hole probes. Surface oil flow visualization and surface static pressure data were also taken. The study was conducted with an inlet Mach number of 0.786. The diffuser Reynolds based on the inlet centerline velocity and the exit diameter of the diffuser was 3,200,000. Comparison of the measured data with previously published computational results are made. Data demonstrating the ability of vortex generators to reduce flow separation and circumferential distortion is also presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-4660 , E-9582 , NAS 1.26:4660
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The Effects of Vortex Ingestion on the Flow in a Diffusing S-duct (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental study of the effects of an ingested vortex on the flowfield of a diffusing S-duct is reported. The vortex is generated through the use of a stationary pinwheel device mounted upstream of the diffusing S-duct. Three test conditions vary the location of the vortex in the duct inlet crossplane. For each condition of ingested vortex, a baseline S-duct and an S-duct with an array of vortex generators is examined. The data taken consist of duct inlet and exit crossplane surveys of velocity and total pressure. Duct surface flow visualization and static pressure are also recorded. The data acquired in these tests are compared to identical S-duct data taken in the absence of the ingested vortex. The ingested vortex is observed to have a strong influence on the flowfield inside (and exiting) the S-duct, but only when the vortex impinges at the inlet crossplane location coincident with the crossplane location of downstream flow separation within the duct. When the ingested vortex impinges at this location it reduces the extent of flowfield separation inside the baseline duct and promotes stronger crossflow in the exit plane of both the baseline duct and the duct with installed vortex generators. This enhanced crossflow also strengthens the vortices shed from the vortex generators. The other impingement locations of the ingested vortex are found to produce little effect on the flowfield of the duct with or without vortex generators.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-106652 , E-8964 , NAS 1.15:106652 , AIAA PAPER 94-2811 , Joint Propulsion Conference; Jun 27, 1994 - Jun 29, 1994; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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