The Experts below are selected from a list of 10500 Experts worldwide ranked by ideXlab platform

Forman A Williams - One of the best experts on this subject based on the ideXlab platform.

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Abstract Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 mm) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 cm/sec to 10 cm/s and initial droplet diameters varied from 1 mm to 3 mm. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    Third Joint Meeting of the U.S. Sections of the Combustion Institute, 2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 microns) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 to 10 centimeters per second and initial droplet diameters varied from 1 to 3 millimeters. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the KC 135 aircraft an electric fan was used to draw a uniform flow past a tethered droplet. Experimental results show that the burn rate increases and the overall flame size decreases with increases in forced-flow velocities over the range of flow velocities and droplet sizes tested. The total radiative heat loss rate, Q(sub r), decreases as the imposed flow velocity increases with the spherically symmetric combustion having the highest values. These observations are in contrast to the trends observed for gas-jet flames in microgravity, but consistent with the observations during flame spread over solid Fuels where the burning rate is coupled to the forced flow as here.

Michael C Hicks - One of the best experts on this subject based on the ideXlab platform.

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Abstract Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 mm) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 cm/sec to 10 cm/s and initial droplet diameters varied from 1 mm to 3 mm. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    Third Joint Meeting of the U.S. Sections of the Combustion Institute, 2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 microns) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 to 10 centimeters per second and initial droplet diameters varied from 1 to 3 millimeters. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the KC 135 aircraft an electric fan was used to draw a uniform flow past a tethered droplet. Experimental results show that the burn rate increases and the overall flame size decreases with increases in forced-flow velocities over the range of flow velocities and droplet sizes tested. The total radiative heat loss rate, Q(sub r), decreases as the imposed flow velocity increases with the spherically symmetric combustion having the highest values. These observations are in contrast to the trends observed for gas-jet flames in microgravity, but consistent with the observations during flame spread over solid Fuels where the burning rate is coupled to the forced flow as here.

Wenming Yang - One of the best experts on this subject based on the ideXlab platform.

  • numerical modeling on a diesel engine fueled by biodiesel Methanol blends
    Energy Conversion and Management, 2015
    Co-Authors: Wenming Yang
    Abstract:

    Abstract A modeling study was conducted to investigate the impact of Methanol addition on the performance, combustion and emission characteristics of a diesel engine fueled by biodiesel. 3-D CFD simulations were conducted using the KIVA4 code coupled with CHEMKIN II for neat biodiesel and its blend Fuels with 5%, 10% and 15% (in vol.) of Methanol under 10%, 50% and 100% loads and a fixed engine speed of 2400 rpm conditions. A skeletal reaction mechanism was developed to mimic the significant species and reaction pathways of biodiesel and Methanol Fuels, and it was validated by performing the ignition delay calculations for biodiesel and Methanol, as well as 3D numerical simulations against the experimental results for biodiesel. Good agreements in terms of ignition delay, cylinder pressure and heat release rate predictions were obtained. The simulation results revealed that with partial replacement of biodiesel by Methanol, tangible improvement on the cylinder pressure was observed under 10% load condition especially for the case with 5% Methanol blend ratio. Whereas, under 50% and 100% engine load conditions, only comparable cylinder pressure curves were seen. In terms of performance characteristics, almost linearly increased indicated thermal efficiency with respect to Methanol blend ratio were observed under all the engine load conditions. Overall, the indicated CO and soot emissions decreased.

Nathan Kaib - One of the best experts on this subject based on the ideXlab platform.

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Abstract Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 mm) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 cm/sec to 10 cm/s and initial droplet diameters varied from 1 mm to 3 mm. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    Third Joint Meeting of the U.S. Sections of the Combustion Institute, 2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 microns) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 to 10 centimeters per second and initial droplet diameters varied from 1 to 3 millimeters. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the KC 135 aircraft an electric fan was used to draw a uniform flow past a tethered droplet. Experimental results show that the burn rate increases and the overall flame size decreases with increases in forced-flow velocities over the range of flow velocities and droplet sizes tested. The total radiative heat loss rate, Q(sub r), decreases as the imposed flow velocity increases with the spherically symmetric combustion having the highest values. These observations are in contrast to the trends observed for gas-jet flames in microgravity, but consistent with the observations during flame spread over solid Fuels where the burning rate is coupled to the forced flow as here.

John Easton - One of the best experts on this subject based on the ideXlab platform.

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Abstract Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 mm) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 cm/sec to 10 cm/s and initial droplet diameters varied from 1 mm to 3 mm. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the

  • radiative heat loss measurements during microgravity droplet combustion in a slow convective flow
    Third Joint Meeting of the U.S. Sections of the Combustion Institute, 2003
    Co-Authors: Michael C Hicks, Nathan Kaib, John Easton, Vedha Nayagam, Forman A Williams
    Abstract:

    Radiative heat loss from burning droplets in a slow convective flow under microgravity conditions is measured using a broad-band (0.6 to 40 microns) radiometer. In addition, backlit images of the droplet as well as color images of the flame were obtained using CCD cameras to estimate the burning rates and the flame dimensions, respectively. Tests were carried out in air at atmospheric pressure using n-heptane and Methanol Fuels with imposed forced flow velocities varied from 0 to 10 centimeters per second and initial droplet diameters varied from 1 to 3 millimeters. Slow convective flows were generated using three different experimental configurations in three different facilities in preparation for the proposed International Space Station droplet experiments. In the 2.2 Second Drop-Tower Facility a droplet supported on the leading edge of a quartz fiber is placed within a flow tunnel supplied by compressed air. In the Zero-Gravity Facility (five-second drop tower) a tethered droplet is translated in a quiescent ambient atmosphere to establish a uniform flow field around the droplet. In the KC 135 aircraft an electric fan was used to draw a uniform flow past a tethered droplet. Experimental results show that the burn rate increases and the overall flame size decreases with increases in forced-flow velocities over the range of flow velocities and droplet sizes tested. The total radiative heat loss rate, Q(sub r), decreases as the imposed flow velocity increases with the spherically symmetric combustion having the highest values. These observations are in contrast to the trends observed for gas-jet flames in microgravity, but consistent with the observations during flame spread over solid Fuels where the burning rate is coupled to the forced flow as here.