Effect of forebody configuration on nonslender delta wing rock
- Paper number
IAC-12,C2,7,13.p1,x14192
- Author
Mr. Bing Han, College of Astronautics,Northwestern Polytechnical University, China
- Coauthor
Prof. Min XU, College of Astronautics,Northwestern Polytechnical University, China
- Coauthor
Mr. Yibin DOU, College of Astronautics,Northwestern Polytechnical University, China
- Coauthor
Mr. Tianxing CAI, College of Astronautics,Northwestern Polytechnical University, China
- Year
2012
- Abstract
Delta wing and sharp/ conical camber forebody profile is commonly used in reusable spacecraft configuration to obtain a balanced aerodynamic performance at wide range of flight speeds. Numerical simulation of forebody/wing rolling accompanied by vortex-vortex disturbance at large angle of attack might help recognize the physical mechanism of nonlinear roll motion and configuration shapes suitable for suppressing roll oscillations. Delta wing/forebody roll motion always produces abundant vortical flow patterns. A coupled computation method consist of RANS equations and Euler equations of rigid-body dynamics is established to predict the nonlinear rock characteristic. The rigid grid rotation method conforms well to geometric conservation law. Large scale multi-processors parallel calculation technique is adopt to reduce computation period. The computation result of amplitude of roll angle and reduced frequency of a 65 degree pure delta wing rock at a given angle of attack accord with the experiment result. Then a 80 degree sharp forebody and a conical camber forebody are placed forward the delta wing apex respectively and simulated. Comparison of their rock characteristic reveals that the forebody-wing interaction obviously affects the critical state and reduced frequency. The aerodynamic spring mechanism of forebody/wing rock is also discussed by analyzing the unsteady flowfield structure.
- Abstract document
- Manuscript document
(absent)