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논문 기본 정보

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학위논문
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김다혜 (부산대학교, 부산대학교 대학원)

지도교수
오세종
발행연도
2021
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이 논문의 연구 히스토리 (4)

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본 연구에서는 시간 효율적 해석 기법인 Actuator Surface Method(ASM)을 활용하여 제자리 비행하는 동축 프로펠러의 공력 해석을 수행하고, 운용조건과 파라미터에 따른 공력 성능과 그 특성을 분석하였다. 동축 프로펠러는 단일 프로펠러 대비 추가적인 설계 변수의 증가와 상/하단 프로펠러 사이의 상호 간섭으로 인하여 실험적/수치적 성능 평가에 비용과 시간 측면에서 여러 제약이 따른다. ASM은 전처리 시간과 격자 수, 해석 소요시간 절감 측면에서 장점을 가지기 때문에, 다양한 운용 조건에서의 동축 프로펠러의 공력 성능 분석에 적합하다. 선행 연구 및 Full CFD와의 비교를 통해 해석 기법의 정확도를 검증하고, 해석 시간 비교를 통하여 ASM의 효율성에 대해 평가하였다. 반회전 프로펠러에서는 축 간극이 증가할수록 상/하단 프로펠러의 상호 간섭이 감소하여 상단 프로펠러의 공력 성능은 단일 프로펠러와 유사한 수준으로 회복되지만, 하단 프로펠러의 상단 프로펠러의 영향으로 인해 공력 성능이 감소한다. 또한 상/하단 회전속도의 변화에서는 상단 프로펠러의 후류가 하단 프로펠러에 직접적인 영향을 주기 때문에, 상단 프로펠러의 회전속도 변화가 고정된 회전속도를 가지는 하단 프로펠러의 성능에 더 큰 영향을 미침을 확인하였다. 동회전 프로펠러에서는 두 프로펠러가 같은 위상을 가지고 회전할 때 가장 성능이 저하되며, 두 프로펠러의 위상차가 작을수록 ASM과 full CFD와의 오차가 증가하였다. 해석 결과를 바탕으로 반회전 프로펠러의 제자리 비행 효율을 분석하고, 단일 프로펠러의 성능으로부터 반회전 프로펠러의 성능을 추정할 수 있는 간단한 예측 인자를 도출하고 ASM의 활용 가능성을 평가하였다. 본 연구를 통해 동축 프로펠러를 활용한 비행체 개발 시 유용하게 활용 가능한 성능 특성 정보와 파라미터를 제시하고, 동축 프로펠러의 공력 해석에 대한 ASM의 유용성을 제시하고자 한다.

목차

1. 서론 ································································································································· 1
1.1. 연구 배경 ····························································································································· 1
1.2. 선행 연구 ····························································································································· 3
1.3. 연구 목표 ····························································································································· 4
2. 해석 방법 ······················································································································· 5
2.1. 수치 해석 기법 ··················································································································· 5
2.2. 해석 형상 및 격자 ············································································································· 7
2.2.1 해석 형상 ······················································································································· 7
2.2.2 해석 격자 ····················································································································· 10
2.3. 해석 조건 ··························································································································· 11
3. 해석 결과 및 분석 ···································································································· 12
3.1. 단일(Single) 프로펠러 ····································································································· 12
3.2. 반회전(Counter-rotating) 프로펠러 ·············································································· 13
3.2.1 선행 연구와의 비교 ··································································································· 13
3.2.2 축 간극의 영향 ··········································································································· 17
3.2.3 회전속도의 영향 ········································································································· 23
3.3. 동회전(Co-rotating) 프로펠러 ······················································································· 26
3.3.1 사이각의 영향 ············································································································· 26
4. Actuator 기법 활용 ··································································································· 29
4.1. 제자리 비행 효율 ············································································································· 29
4.2. 공력 성능 예측 계수 ······································································································· 32
5. 결론 ······························································································································ 35
참고문헌 ···························································································································· 36
Abstract ····························································································································· 40

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