We found a match
Your institution may have access to this item. Find your institution then sign in to continue.
- Title
A SPINNING TAIL MISSILE CFD AERODYNAMIC STUDY.
- Authors
Ioan, Calimanescu; Lucian, Grigorescu
- Abstract
Applied aerodynamics has, historically, involved a very strong mix of theory and experiment. This is partly because experiments can be very costly and computations are rarely sufficiently sophisticated. This will continue to be the case. Computational Fluid Dynamics (CFD) is playing an ever increasing role in aerodynamic design for advanced missiles either for performance improvement of the existing system for new missions or for new concept development for future missions. A cost effective design process is to judiciously combine the wind tunnel tests and CFD studies that exploit the inherent strengths of each of these. The objective of the current paper is to present a reliable CFD advanced technique for obtaining supersonic spinning tail missile aerodynamics. In achieving this goal state of the art software was involved: Fluent 6.1, along with all its facilities. As simulation scenarios, were considered four missile spinning tail angular velocities corresponding to 500, 1000, 1500 and 2000 rpm and a comparative study of computed results was conducted. The outcome of this paper should be a comprehensive and exhaustive study in CFD sense, of this special class of missiles.
- Subjects
AERODYNAMICS; COMPUTATIONAL fluid dynamics; COST effectiveness; SPACE environment; FLUID mechanics
- Publication
Annals (Constanţa Maritime University), 2011, Vol 12, Issue 16, p103
- ISSN
2067-0427
- Publication type
Article