Department News
Aerodynamic Shape Optimization : Exploring the Limits of Design
Seminar Date
2003-07-02
Author
정기훈
Date
2003-07-02
Views
1609
1. 제 목 : Aerodynamic Shape Optimization : Exploring the Limits of Design
2. 연 사 : Dr. Sangho Kim (Stanford University)
3. 일 시 : 2003년 7월 8일 (화) 16:00 - 18:00
4. 장 소 : 서울대 신공학관(301동) 117호 세미나실
5. 내 용 :
Recently wing planform parameters have been included as design variables and Aerospace Computing Laboratory has successfully designed a wing of the aircraft configuration which produces a specified lift with minimum drag, while meeting other criteria such as low structure weight, sufficient fuel volume, and stability and control. Based on the promising results from our wing planform optimization strategy applied to inviscid flow and from our viscous aerodynamic design techniques, in the present work the wing shape and planform optimization methods is applied to viscous flow.
Meanwhile, the design method, which is greatly accelerated by the use of control theory, is adjoint gradient formula. The computational savings in gradient calculation are particularly significant for 3-D aerodynamic shape optimization problems on general unstructured and overset meshes. The use of unstructured grid techniques hold considerable promise for aerodynamic design by facilitating the treatment of complex configurations without incurring a prohibited cos and bottleneck in mesh generation. The computational feasibility of using unstructured meshes is enabled by the use of the continuous adjoint approach and the reduced gradient formulas.
6. 약 력 :
1992 이학사 (경희대학교 우주과학과
1995 Master of Science (Aeronautics & Astronautics, Stanford University)
2001 Ph.D. (Aeronautics & Astronautics, Stanford University)
2001-현재 Post-Doctoral (Stanford University)
7. 문 의 : 기계항공공학부 김종암 교수 (☏ 880-1915)
2. 연 사 : Dr. Sangho Kim (Stanford University)
3. 일 시 : 2003년 7월 8일 (화) 16:00 - 18:00
4. 장 소 : 서울대 신공학관(301동) 117호 세미나실
5. 내 용 :
Recently wing planform parameters have been included as design variables and Aerospace Computing Laboratory has successfully designed a wing of the aircraft configuration which produces a specified lift with minimum drag, while meeting other criteria such as low structure weight, sufficient fuel volume, and stability and control. Based on the promising results from our wing planform optimization strategy applied to inviscid flow and from our viscous aerodynamic design techniques, in the present work the wing shape and planform optimization methods is applied to viscous flow.
Meanwhile, the design method, which is greatly accelerated by the use of control theory, is adjoint gradient formula. The computational savings in gradient calculation are particularly significant for 3-D aerodynamic shape optimization problems on general unstructured and overset meshes. The use of unstructured grid techniques hold considerable promise for aerodynamic design by facilitating the treatment of complex configurations without incurring a prohibited cos and bottleneck in mesh generation. The computational feasibility of using unstructured meshes is enabled by the use of the continuous adjoint approach and the reduced gradient formulas.
6. 약 력 :
1992 이학사 (경희대학교 우주과학과
1995 Master of Science (Aeronautics & Astronautics, Stanford University)
2001 Ph.D. (Aeronautics & Astronautics, Stanford University)
2001-현재 Post-Doctoral (Stanford University)
7. 문 의 : 기계항공공학부 김종암 교수 (☏ 880-1915)
