Analysis of Boundary-Layer Transition Measurements on a Blunt Ogive at the Holloman Sled Track
Abstract
Accurate prediction of boundary-layer transition remains critical to the design of hypersonic vehicles, due to the dramatic effect of transition on heat transfer, boundary-layer separation, and aerodynamic control authority. Although much progress has been made in understanding the basic mechanisms of transition, vehicle designers usually predict transition using simple correlations. The uncertainties in these correlations are large for a new hypersonic vehicle, generating high levels of development risk and tendencies towards less-effective but conservative designs. Furthermore, no single ground test can simulate all aspects of hypervelocity transition, and nearly all ground tests are corrupted by the high levels of test-section noise in conventional hypersonic wind tunnels. Mechanism-based prediction methods are needed for effective design of flight vehicles, and measurements of the mechanisms of transition are needed as part of a larger team effort to develop and validate these methods.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Feb 29, 2024
- Source ID
- FA95502310237
Entities
People
- Steven Schneider
Organizations
- Air Force Office of Scientific Research
- Purdue University
- United States Air Force