Friction Drag and Shock Load Estimation on Re-entry Capsules and Spaceplane Using Pressure Sensitive Paint Coupled with Free-Flight Force Measurement
Abstract
A new experimental technique is proposed to extract friction drag from total aerodynamic force acting on a hypersonic wind tunnel model. The friction drag would be a useful measure to predict near-wall structure of complex flows such as laminar-turbulent boundary layer and its transition which has a great influence on aerodynamic heating and drag estimation of a hypersonic body. However, prediction of the friction drag from experiments is still challenging because no diagnostic can measure it directly.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Feb 16, 2024
- Source ID
- FA23862314095
Entities
People
- Hidehiro Hata
Organizations
- Air Force Office of Scientific Research
- Kumamoto University
- United States Air Force