The Experts below are selected from a list of 249 Experts worldwide ranked by ideXlab platform

J Kitajima - One of the best experts on this subject based on the ideXlab platform.

  • Research on a Methane-Fueled Low NO[sub x] Combustor for a Mach 3 Supersonic Transporter Turbojet Engine
    Journal of Engineering for Gas Turbines and Power, 2001
    Co-Authors: Y. Kinoshita, T. Oda, J Kitajima
    Abstract:

    Methane-fueled low NOx combustor research had been conducted tinder the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet engine. Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion characteristics in the first phase of the research. A single can-type combustor was fabricated and high-temperature and high-pressure combustion tests were carried out for the evaluation on NOx emission reduction capability of the PJSC concept in the second phase. In the final phase of research, a multisector combustor was fabricated and the performance demonstration test was conducted for the final evaluation of the pollutant exhaust emission goals and the combustor performance goals set in the HYPR project. The sequential three-phased program tvas completed successfully, and the project goals of NOx emission, combustion efficiency, pressure loss and exit gas temperature pattern factor at the Mach 3 Cruise Condition, together with the ICAO regulatory levels fbr supersonic aircraft at LTO Conditions, were all achieved in the performance demonstration test.

Y. Kinoshita - One of the best experts on this subject based on the ideXlab platform.

  • Research on a Methane-Fueled Low NO[sub x] Combustor for a Mach 3 Supersonic Transporter Turbojet Engine
    Journal of Engineering for Gas Turbines and Power, 2001
    Co-Authors: Y. Kinoshita, T. Oda, J Kitajima
    Abstract:

    Methane-fueled low NOx combustor research had been conducted tinder the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet engine. Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion characteristics in the first phase of the research. A single can-type combustor was fabricated and high-temperature and high-pressure combustion tests were carried out for the evaluation on NOx emission reduction capability of the PJSC concept in the second phase. In the final phase of research, a multisector combustor was fabricated and the performance demonstration test was conducted for the final evaluation of the pollutant exhaust emission goals and the combustor performance goals set in the HYPR project. The sequential three-phased program tvas completed successfully, and the project goals of NOx emission, combustion efficiency, pressure loss and exit gas temperature pattern factor at the Mach 3 Cruise Condition, together with the ICAO regulatory levels fbr supersonic aircraft at LTO Conditions, were all achieved in the performance demonstration test.

Teng-kuei Su - One of the best experts on this subject based on the ideXlab platform.

  • SESSION TITLE: Drive-By-Noise Study of Tire Noise for Vehicle Noise Control
    2020
    Co-Authors: Yu-ying Chen, Teng-kuei Su
    Abstract:

    Most popular method to control vehicle noise is to limit acceleration noise. Perform acceleration, Cruise and coast test, to evaluate the tire noise contribution to acceleration and Cruise noise. For car, tire noise is 20 ~ 50 % contribution to acceleration. However, for large vehicle, the tire noise contribution is lower. Nevertheless, tire noise contribution reach 80 ~ 100 % in Cruise Condition at 80 and 100 km/h. Base on 109 samples, tire noise is positive correlation to tire width. During vehicle type approval, wider tire of all options for vehicle should be used. It is possible to predict on road noise from in lab test

  • Study of Tire Noise for Vehicle Noise Control
    SAE Technical Paper Series, 2005
    Co-Authors: Jeff S. C. Chuang, Yu-ying Chen, Teng-kuei Su
    Abstract:

    Most popular method to control vehicle noise is to limit acceleration noise. Perform acceleration, Cruise and coast test, to evaluate the tire noise contribution to acceleration and Cruise noise. For car, tire noise is 20 ~ 50 % contribution to acceleration. However, for large vehicle, the tire noise contribution is lower. Nevertheless, tire noise contribution reach 80 ~ 100 % in Cruise Condition at 80 and 100 km/h. Base on 109 samples, tire noise is positive correlation to tire width. During vehicle type approval, wider tire of all options for vehicle should be used. It is possible to predict on road noise from in lab test

T. Oda - One of the best experts on this subject based on the ideXlab platform.

  • Research on a Methane-Fueled Low NO[sub x] Combustor for a Mach 3 Supersonic Transporter Turbojet Engine
    Journal of Engineering for Gas Turbines and Power, 2001
    Co-Authors: Y. Kinoshita, T. Oda, J Kitajima
    Abstract:

    Methane-fueled low NOx combustor research had been conducted tinder the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet engine. Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion characteristics in the first phase of the research. A single can-type combustor was fabricated and high-temperature and high-pressure combustion tests were carried out for the evaluation on NOx emission reduction capability of the PJSC concept in the second phase. In the final phase of research, a multisector combustor was fabricated and the performance demonstration test was conducted for the final evaluation of the pollutant exhaust emission goals and the combustor performance goals set in the HYPR project. The sequential three-phased program tvas completed successfully, and the project goals of NOx emission, combustion efficiency, pressure loss and exit gas temperature pattern factor at the Mach 3 Cruise Condition, together with the ICAO regulatory levels fbr supersonic aircraft at LTO Conditions, were all achieved in the performance demonstration test.

Kenji Yoshida - One of the best experts on this subject based on the ideXlab platform.

  • numerical analysis on flight test results of supersonic experimental airplane nexst 1
    Journal of Aircraft, 2007
    Co-Authors: Hiroaki Ishikawa, Dongyoun Kwak, Kenji Yoshida
    Abstract:

    A flight test of a supersonic experimental airplane (National Experimental Supersonic Transport, NEXST-1) was successfully conducted by the Japan Aerospace Exploration Agency in October of 2005. The experimental airplane was designed to reduce drag on supersonic Cruise Condition by means of some conventional and advanced design concepts: arrow wing planform, warp wing, area-ruled body, and natural laminar flow wing. The purpose of this study was to make clear the verification of those design concepts on the experimental airplane using the computational fluid dynamics analysis. The computational fluid dynamics results were compared with the flight-test results. The aeroelastic deformation and boundary layer transition were taken into account in the computational fluid dynamics analysis. This comparison highlighted the quantitative benefit of the natural laminar flow wing design concept. Furthermore, a real size supersonic transport could be designed using the drag reduction design technologies already validated from the NEXST-1 flight test. The results helped clarify the net drag reduction potentially attainable on a full-scale supersonic transport.

  • Boundary Layer Transition Measurement using Preston tube on NEXST-1 Flight Test
    25th AIAA Applied Aerodynamics Conference, 2007
    Co-Authors: Dongyoun Kwak, Kenji Yoshida, Masayoshi Noguchi, Hiroaki Ishikawa
    Abstract:

    Flight test of a supersonic experimental airplane (NEXST-1) was performed to improve advanced aerodynamic design technologies for next generation SST. The drag reduction on the supersonic Cruise Condition is set to a goal on the aerodynamic design of the NEXST-1. Aerodynamic data in the flight test were measured to validate the aerodynamic design concepts. Boundary layer transition locations were measured using the Preston tube to directly validate the natural laminar flow wing design concept. The measurement system and the flight test results were reported in this paper. The Preston tubes could detect the boundary layer transition locations. Boundary layer transition locations were most delayed on a design point than that’s on the off-design points. It can be confirmed that the natural laminar flow wing design concepts in the flight test. Nomenclature

  • flight test measurements of surface pressure on unmanned scaled supersonic experimental airplane
    24th AIAA Applied Aerodynamics Conference, 2006
    Co-Authors: Dongyoun Kwak, Kenji Yoshida, Hiroaki Ishikawa, Masayoshi Noguchi
    Abstract:

    Flight test of a supersonic experimental airplane was performed by Japan Aerospace Exploration Agency to improve advanced aerodynamic design technologies for next generation SST. The experimental airplane was designed for reduction of the drag on supersonic Cruise Condition. A lot of aerodynamic data in the flight test were obtained to validate the aerodynamic design concepts. High quality static pressure measurement systems were constructed to obtain the static pressure distributions. The pressure coefficient distributions in the flight test corresponded with CFD results that were target distributions obtained by optimum design. The pressure results were also consistent with the transition results and aerodynamic force characteristics in the flight test. Aerodynamic design concepts for drag reduction were demonstrated qualitatively and quantitatively by the NEXST-1 flight test.