면내 곡률이 있는 날개의 공력 및 플러터 해석

다국어 초록 (Multilingual Abstract)

Long-range international air travel has increased significantly and will continue to
increase well. This trend and advances in flight technologies, such as aircraft structures,
materials, propulsion, and electronics, have resulted in a renewed interest in supersonic
cruise aircraft. The concept of curving the leading and trailing edges of the wings can
improve aerodynamic performance and reduce the pitch-up instability associated with highly
swept wings. Computational fluid dynamics (CFD) and time-domain flutter analyses have
been conducted to investigate the effects of planform curvature (curving the leading and
trailing edges of a wing in the x-y plane) on both aerodynamic and flutter characteristics of a
series of three moderately swept-back wing models. For three-different wing models,
moderate angle-of-attack conditions corresponding to cruise flight and high angle-of-attack
conditions to landing are considered in this study. In addition, effective time-domain flutter
analyses based on transonic small-disturbance equations have been conducted and compared
with previous NASA wind-tunnel flutter test.

목차 (Table of Contents)

• 목 차 ⅱ
• 표 목차 ⅲ
• 그림 목차 ⅲ
• ABSTRACT ⅶ
• Ⅰ. 서 론 7
• 1.1 연구배경 및 목적 7
• 1.2 문헌조사 8
• Ⅱ. 이론적 배경 10
• 2.1 연속체기반 전산유체역학 지배방정식 10
• 2.2 난류모델 11
• 2.3.1 Spalart-Allmaras(S-A) 11
• 2.3.2 Shear-Stress Transport(SST) k-ω 13
• Ⅲ. 해석결과 및 검토 16
• 3.1 Biconvex 에어포일 형상 유동해석 및 검증 16
• 3.2 면내 곡률이 있는 날개의 저받음각 공력 해석 27
• 3.3 면내 곡률이 있는 날개의 고받음각 공력 해석 112
• 3.4 면내 곡률이 있는 날개의 플러터 해석 및 검증 127
• Ⅳ. 결 론 144
• 참고문헌 146