並列タイトル等Ignition of Solid Fuels and Propellants in a Hot Stagnation-Point Flow
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-584
一般注記The ignition times of solid propellant binders and their composite-propellants in a hot stagnation point flow are measured experimentally. The specimens of 2×10(exp -2)m diameter hemisphere are HTPB, CTPB and solid propellants composed of their binders. External flow temperatures are 950 to 1175K, flow velocities are 3.5 to 20m/sec and oxygen volume percentages in a flow are 20％ to 100％. The ignition characteristics of binders are strongly left in ignition of composite-propellants, and the ignition times of the HTPB propellant are longer than those of the CTPB propellant. The ignition time of solid fuels shortens as flow velocity increases with a constant flow temperature, but at higher velocities the ignition time grows longer again and there is a critical velocity at which ignition can not take place. This phenomenon is a characteristic of gas-phase ignition of solid fuels in this flow field and it is analysed by using an approximate thermal theory in the appendix.
資料番号: NALTR0584000
レポート番号: NAL TR-584
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ