Towards a Mechanism-Based Procedure for Predicting Boundary-Layer Transition on Slender Models with Highly Swept Fins: Further Mach-6 Quiet-Tunnel Measurements
Abstract
Slender geometries with highly swept fins continue to be of interest to the Dept. of Defense for boost-glide hypersonic strike vehicles and other applications. Laminar-turbulent transition on these vehicles is critical because of the effect on heat transfer, boundary-layer separation, and other phenomena. The highly swept fins introduce at least two new instability-related phenomena thatmust be better understood to improve transition predictions: (1) the interaction of the highly swept fin-shock with the boundary layer on the body, and (2) the stream wise corner flow between the fin and body.Here, we propose to continue to study these phenomena using a generic straight circular cone, with a single fin. We propose further studies of a few select geometries, in greater detail. We plan to focus on the 1/8-inch fin radius, the 7-deg. half-angle cone, and the largest fin sweep (smallest fin) that yields good measurements at feasible quiet Reynolds numbers (70 to 80 degrees), with transition occurring towards the aft end of the model. We also plan to study only two nose radii: 0 and either 1 or 2 mm, depending on observed effects. This reduces the parameter space, which increases the feasible level of detail for each geometry to be tested. The final selections are to be made after discussion with the program manager and our computational colleagues.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Aug 15, 2019
- Source ID
- N000141912499
Entities
People
- Steven Schneider
Organizations
- Office of Naval Research
- United States Navy
- University of Virginia