Calculation of Dual-Mode Engine Performance

スポンサーリンク

概要

• 論文の詳細を見る

• Thrust performance and operating conditions of a dual-mode engine were calculated with a one-dimensional flow model. Pseudo-shock in the isolator in the ramjet mode was modeled with the momentum balance model. The decelerated air at the end of the pseudo-shock showed the highest pressure in the engine in the ramjet mode. The effects of height of the inflow boundary layer, combustion efficiency, and angle of attack were investigated. Larger thrust was produced with larger angle of attack, while specific impulse was unaffected by the angle of attack but by the contraction ratio of the engine. A small change in the combustion efficiency induced a large change in the position of the pseudo-shock in the isolator. Thrust in the ramjet mode was almost the same as that in the scramjet mode at the same flight Mach number.

• 社団法人 日本航空宇宙学会の論文
• 2006-02-04

著者

• Kudo Kenji

  Combined Propulsion Research Group Japan Aerospace Exploration Agency

• KANDA Takeshi

  Combined Propulsion Research Group, Japan Aerospace Exploration Agency

• TANI Kouichiro

  Combined Propulsion Research Group, Japan Aerospace Exploration Agency

• KATO Kanenori

  Combined Propulsion Research Group, Japan Aerospace Exploration Agency

• Kudo Kenji

  Combined Propulsion Research Group, Japan Aerospace Exploration Agency

関連論文

• Staging of Two-Stage-to-Orbit Aerospace Plane
• Calculation of Dual-Mode Engine Performance
• Effect of Sides-spillage from Airframe on Scramjet Engine Performance

スポンサーリンク