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논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- 최정열
- 발행연도
- 2014
- 저작권
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Recently, various aspects of Ramjet research is on progress. However, most of them are related to supersonic air intake. This paper assumed engine is installed at the end of supersonic air intake and investigated air supply process.
By using well-known basic compressible flow dynamics and physics, program for designing air intake which operates at supersonic speed has been built. Shape of supersonic air intake is designed through the program with post-processing and packaging ability. It has been proven with CFD through 1-D result value calculation.
Result value and shape comfirmed by program has been applied well to CFD and operation was good. Normal shock forming inside was not estimated well. This is due to reflection shock which is not considered in the program.
Also, when comparing results of non-viscosity and viscosity cases, most of the results excluding the reflection shock are similar for both cases. This result is important because it indicates the concept design program is applicable to actual design.
Various design cases were investigated to modify the location of normal shock due to the unexpected reflection shock. When area ratio was 1.5 the location of calculated normal shock is similar to the result from CFD. Additionally, relation ship between trend of normal shock location and flight mach number has been found. This was set as modification value and has been added to the concept design program. As a result, withini negligible error, location of normal shock was identifiable.
By using well-known basic compressible flow dynamics and physics, program for designing air intake which operates at supersonic speed has been built. Shape of supersonic air intake is designed through the program with post-processing and packaging ability. It has been proven with CFD through 1-D result value calculation.
Result value and shape comfirmed by program has been applied well to CFD and operation was good. Normal shock forming inside was not estimated well. This is due to reflection shock which is not considered in the program.
Also, when comparing results of non-viscosity and viscosity cases, most of the results excluding the reflection shock are similar for both cases. This result is important because it indicates the concept design program is applicable to actual design.
Various design cases were investigated to modify the location of normal shock due to the unexpected reflection shock. When area ratio was 1.5 the location of calculated normal shock is similar to the result from CFD. Additionally, relation ship between trend of normal shock location and flight mach number has been found. This was set as modification value and has been added to the concept design program. As a result, withini negligible error, location of normal shock was identifiable.
목차
차례 i그림 목록 iii표 목록 v기호 설명 vi1. 서론 12. 초음속 공기 흡입구 설계 42.1. 초음속 공기 흡입구 설계 이론 82.1.1. 비행 고도 조건 82.1.2. 초음속 흡입구 유동 개요 92.1.3. 2차원 경사 충격파 유동 관계식 112.1.4. 원추형 경사 충격파 유동 관계식 122.1.5. 점성효과 보정 212.2. 초음속 공기 흡입구 이론 설계 및 성능 해석 프로그램 232.2.1. 설계프로그램 범위 232.2.2. 설계프로그램 개요 242.2.3. 설계 변수 252.2.4. Wedge (Cone) 각도 결정 262.2.5. External, Circular, Throat, Diffuser 구성 비율 262.2.6. Terminal Normal Shock 상태별 계산 방법 292.2.6.1. Above design 292.2.6.2. On design 292.2.6.3. Below design 302.3. 설계 결과 323. 전산 유체 해석을 이용한 설계 검증 353.1. 유동장 모델링 353.1.1. Navier-Stokes 방정식 353.1.2. 난류모델 373.2. 수치 해석 기법 403.2.1. 공간에 따른 해석 방법 403.2.1.1. 수치 플럭스 473.2.1.2. 고차 정확도 공간차분 483.2.1.2.1. MUSCL-TVD 493.2.2. 시간에 따른 해석 방법 (시간 적분 기법) 493.3. 격자 생성 및 해석 조건 533.3.1. 2-block 533.3.2. 경계 및 초기 조건 533.3.3. 계산 환경 543.4. 해석 결과 544. 결론 655. 참고문헌 66
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