Report Number: R16E0120 Responsible Representative: Takashi Kubota(Research and Development Directorate, Research Unit I) Contact Information: Takahiro Nakamura(nakamura.takahiro@jaxa.jp) Members: Seiji Tsutsumi, Hiroyuki Ito, Takahiro Nakamura Subject Category: Space(Rocket) Abstract The SS-520 No.4 has the performance to launch the 3 kg mass microsatellite 'TRICOM-1' into the low earth orbit. This rocket launched at 15 January 2017 [JST] however satellite could not be into the orbit due to the rocket system anomaly. According to 1st stage flight results, the flight trajectory and impact・・・<<read more>>
Report Number: R16E0077 Responsible Representative: Takumi Ujino(Technical Counselor) Contact Information: Takanori Haga(haga.takanori@jaxa.jp) Members: Seiji Tsutsumi, Hiroyuki Ito, Masaharu Abe, Takanori Haga Subject Category: Basic Research(Modeling,CFD) Abstract Prediction accuracy of turbulent flows in high Reynolds number is important for aerospace fluid problems. The conventional RANS model is not sufficient for accurately predicting separation and reattachment of the boundary layer and its transition. On the other hand, the computational cost of LES which resolves to small scale vortices near the wall is・・・<<read more>>
Report Number: R16E0112 Responsible Representative: Yuichi Matsuo(Aeronautical Technology Directorate, Numerical Simulation Research Unit) Contact Information: Rui Toyonaga(toyonaga.l.0121@ruri.waseda.jp) Members: Rui Toyonaga Subject Category: Basic Research(Numerical analysis) Abstract For the development of the air breathing engine combustor in space plane,we develop the chemical reaction flow calculation code using the Flamelet Approach. In order to evaluate this code insupersonic region, a verification is performed on the experimental data of the strut-injection supersonic combustion flow field designed by German Aerospace Center. Goal For the・・・<<read more>>
