Report Number: R16E0109 Responsible Representative: Hisao Futamura(Aeronautical Technology Directorate, Propulsion Research Unit) Contact Information: Seiji Yoshida(yoshida.seiji@jaxa.jp) Members: Seiji Yoshida, Mitsumasa Makida, Naoki Nakamura, Takeishi Ikumi Subject Category: Aviation(Aircraft engine) Abstract Lean combustion is promising to reduce nitrogen oxide emission from jet-engines. To solve combustion instability, that is a problem of lean combustion, a pilot burner for ensuring stable combustion and a main burner for performing lean, low-NOx combustion are used. The purpose of this study is improvement of combustor performance・・・<<read more>>
Report Number: R16E0108 Responsible Representative: Yuichi Matsuo(Aeronautical Technology Directorate, Numerical Simulation Research Unit) Contact Information: Takashi Ishida(ishida.takashi@jaxa.jp) Members: Toru Yamaya Subject Category: Basic Research(Numerical analysis,CFD) Abstract The purpose of this study is to construct a fast unsteady CFD (Computational Fluid Dynamics) method with LBM (Lattice Boltzmann Method). Comparisons with SRT (Single-Relaxation Time) and CLBM (Cascaded-LBM) that are collision models are conducted in terms of the stability and the calculation time through the calculation of doubly periodic shear layer with a・・・<<read more>>
Report Number: R16E0106 Responsible Representative: Yuichi Matsuo(Aeronautical Technology Directorate, Numerical Simulation Research Unit) Contact Information: Yuya Ohmichi(ohmichi.yuya@jaxa.jp) Members: Gunpei Morikami Subject Category: Basic Research(Numerical analysis,Modeling) Abstract In this study, coherent structures around a reentry capsule were investigated using the unsteady flow solver FaSTAR. The flow field around a reentry capsule is important because the dynamic instability occurs especially insubsonic cruise. We studied the dynamic instability by numerically simulating the unsteady flow fields around the reentry capsule. Goal To clarify unsteady・・・<<read more>>
Report Number: R16E0105 Responsible Representative: Yuichi Matsuo(Aeronautical Technology Directorate, Numerical Simulation Research Unit) Contact Information: Hidekazu Yoshida(gooden85@fuji.waseda.jp) Members: Tsukasa Nagao, Hidekazu Yoshida Subject Category: Aviation(Aircraft engine) Abstract JAXA is developing the hypersonic turbojet which work at less than Mach 1 to Mach 5. The intake of the hypersonic turbojet reduces air speed and compresses air which is captured by the intake. We conducted the CFD analysis to understand these flow field and operating condition and develop higher efficiency hypersonic turbojet.・・・<<read more>>
