@techreport{oai:jaxa.repo.nii.ac.jp:00043437,
 author = {石黒, 登美子 and 小川, 哲 and 和田, 安弘 and Ishiguro, Tomiko and Ogawa, Satoru and Wada, Yasuhiro},
 month = {Nov},
 note = {Numerical simulations of reacting flowfields in 2/3-dimensional rectangular scramjet combustors with rearward facing steps are presented. They have been carried out by a procedure which was developed to analyze chemically reacting flow with the Harten-Yee typed TVD scheme. This is based on the complete Navier-Stokes equations and chemical species transport equations, including Rogers' combustion model with two reaction stages, Baldwin-Lomax two layer algebraic eddy viscosity model and diffusion coefficients based on Fick's law. A combustor model in the present calculation is a rectangular scramjet combustor with two rearward facing steps and nine transverse injections of hydrogen, which is used in the experiments by Kakuta branch of National Aerospace Laboratory. First, using a profile in the symmetric plane of the model, a 2-dimensional computation to analyze it's flowfield has been executed refinely. Next, 3-dimensional computations of the combustors have also been done rather roughly within the scope of available computer resources Results of these computations are described and the calculated pressure distributions on the wall of the symmetric plane are compared with experimental data., 資料番号: NALSP0014004, レポート番号: NAL SP-14},
 title = {スクラムジェットエンジンの流れ計算},
 year = {1990}
}