HyShot-Ⅱ 스크램제트 연소기 설계 조건에 대한 3차원 전산해석 = Three-Dimensional Numerical Analysis of HyShot-Ⅱ Scramjet Combustor at Design Condition

다국어 초록 (Multilingual Abstract)

HyShot-Ⅱ scramjet combustor flowfield, where gaseous hydrogen is transversely injected into a supersonic cross flow, is numerically investigated using detached-eddy simulation and finite-rate chemistry model. The amount of fuel injection is considered for the design condition which corresponds to equivalence ratio of 0.3. This work features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the pervious studies. Results indicate that fuel-air mixing is caused by Kelvin-Helmholtz instability and enhanced by the impingement of oblique shocks at the fuel-air interface. While the numerical results reproduce well the pressure distribution for non-reacting region and self-ignition location, the pressure rise by combustion is over-predicted.

목차 (Table of Contents)

• ABSTRACT
• 1. 서론
• 2. 수치적 접근 방법
• 3. 계산 결과 및 고찰
• 4. 결론
• 후기
• 참고문헌