운용 특성을 고려한 극초음속 웨이브라이더 설계 기법 연구 = A Study on the Design Method of Hypersonic Waveriders Considering Operational Characteristics

다국어 초록 (Multilingual Abstract)

The design of hypersonic vehicles focuses on achieving superior aerodynamic performance, and the waverider is attracting attention as a key design method for this. Among the design variables of a waverider, the shock wave angle is a key design variable because it can significantly affect lift and drag, but the method for setting it is not known. In addition, extreme aerodynamic heating occurs due to the infinitely sharp leading edge, and the application of a blunt leading edge is essential due to practical limitations such as difficulties in actual manufacturing. Therefore, in this study, the geometry was designed by changing the shock wave angle at the design point conditions of Mach 6.0 and an altitude of 26.4 km, based on the osculating cone waverider. To compare the performance of the geometries under the same conditions, the length, width, and volume of each model were set to be the same. Afterward, using computational analysis, the aerodynamic characteristics were analyzed at off-design points where the Mach number, angle of attack, and sideslip angle were changed, and a basis for setting the shock wave was presented. Also, considering the application of a blunt leading edge to the waverider, the cone tracing method was presented as a design method that enables increased volumetric efficiency and reduced drag. The design point was set to Mach 10.0 and an altitude of 33.5 km by referring to the conditions of the NASA X-43 third flight test, and the length, width, and volume of the two models were set to be the same. The volumetric efficiency was compared for the case with a theoretical (Sharp) geometry and the case with a blunt leading edge (Blunted), and the lift-to-drag ratio at the design point was compared through computational analysis.

국문 초록 (Abstract)

극초음속 비행체의 설계는 뛰어난 공력 성능을 확보하는 데 중점을 두고 있으며 웨이브 라이더는 그에 대한 핵심적인 설계법으로 주목받고 있다. 웨이브라이더의 설계 변수 중 충 격파 각도는 양력과 항력에 크게 영향을 미칠 수 있어 핵심적인 설계 변수이지만, 이에 대 한 설정법은 알려지지 않았다. 또한 무한히 날카로운 앞전으로 인해 극심한 공력 가열이나 제작의 어려움 등과 같은 실용적 한계점들이 존재하며 따라서 무딘 앞전 적용은 필수적이 다. 따라서 본 연구에서는 마하수 6.0, 고도 26.4 km의 설계점 조건에서 접촉 원추 웨이브 라이더의 길이와 너비, 부피가 동일하도록 충격파 각도를 변경하였다. 이후 전산해석을 활 용하여 마하수와 받음각, 옆미끄럼각이 변경된 비설계점에서의 공력 특성을 분석하여 충격 파 설정에 활용될 수 있는 설정 근거를 제시하였다. 또한 웨이브라이더에 대해 무딘 앞전 적용을 고려하여 체적 효율 증가와 항력 감소를 가능하게 하는 설계법인 원추 추적 기법을 제시하였다. 마하수 10.0, 고도 33.5 km의 설계점에서 기존의 접촉 원추 웨이브라이더와 원추 추적 웨이브라이더를 길이와 너비, 부피가 동일하도록 설계하였다. 이후 두 모델이 이 론적(Sharp) 형상을 가질 경우와, 무딘 앞전이 적용된(Blunted) 경우에 대해 체적 효율을 비교하였으며 전산 해석을 활용해 설계점에서의 양항비를 비교하였다.

다국어 초록 (Multilingual Abstract)

The design of hypersonic vehicles focuses on achieving superior aerodynamic performance, and the waverider is attracting attention as a key design method for this. Among the design variables of a waverider, the shock wave angle is a key design variable because it can significantly affect lift and drag, but the method for setting it is not known. In addition, extreme aerodynamic heating occurs due to the infinitely sharp leading edge, and the application of a blunt leading edge is essential due to practical limitations such as difficulties in actual manufacturing. Therefore, in this study, the geometry was designed by changing the shock wave angle at the design point conditions of Mach 6.0 and an altitude of 26.4 km, based on the osculating cone waverider. To compare the performance of the geometries under the same conditions, the length, width, and volume of each model were set to be the same. Afterward, using computational analysis, the aerodynamic characteristics were analyzed at off-design points where the Mach number, angle of attack, and sideslip angle were changed, and a basis for setting the shock wave was presented. Also, considering the application of a blunt leading edge to the waverider, the cone tracing method was presented as a design method that enables increased volumetric efficiency and reduced drag. The design point was set to Mach 10.0 and an altitude of 33.5 km by referring to the conditions of the NASA X-43 third flight test, and the length, width, and volume of the two models were set to be the same. The volumetric efficiency was compared for the case with a theoretical (Sharp) geometry and the case with a blunt leading edge (Blunted), and the lift-to-drag ratio at the design point was compared through computational analysis.

목차 (Table of Contents)

• 1. 서론 1
• 1.1 연구 배경 1
• 1.2 연구 동향 9
• 1.3 연구 목표 14
• 2. 연구 방법 17
• 2.1 전산해석 기법 17
• 2.2 전산해석 기법 검증 24
• 2.3 격자 의존성 분석 27
• 3. 웨이브라이더의 충격파 각도에 따른 성능 연구 29
• 3.1 설계 기법 29
• 3.2 형상 설계 31
• 3.3 설계 기법 검증 40
• 3.4 전산해석 결과 42
• 4. 무딘 앞전 적용을 고려한 웨이브라이더 설계 기법 연구 61
• 4.1 설계 기법 61
• 4.2 형상 설계 65
• 4.3 전산해석 결과 74
• 5. 결론 84
• 참고문헌 86