High-Mach Capability of a Compact External-Compression Intake via Bleed Integration
11th International Conference on Recent Advances in Air and Space Technologies, Conference Program, RAST 2026, İstanbul, Turkey, 13 - 15 May 2026, (Full Text)
- Publication Type: Conference Paper / Full Text
- Doi Number: 10.1109/rast69551.2026.11672368
- City: İstanbul
- Country: Turkey
- Keywords: boundary-layer bleed, external-compression supersonic intake, intake sizing, pressure recovery, RANS, shock-wave/boundary-layer interaction
- Middle East Technical University Affiliated: Yes
Abstract
The design of external-compression supersonic intakes for multi-mission platforms entails a fundamental trade-off between high-speed capability and geometric compactness. Conventional sizing for the maximum flight Mach number increases the required capture area and frontal dimensions, which in turn penalize weight, installation, and spillage drag at lower supersonic conditions. This study numerically investigates the high-Mach capability of a compact single-ramp intake designed for Mach 1.6 and operated up to Mach 1.9 through integration of a boundary-layer bleed system. Reynolds-averaged Navier-Stokes simulations - validated against wind-tunnel measurements of pressure recovery and surface static pressure - are used to assess shock structure, pressure recovery, and operability. The bleed system mitigates shock-wave/boundary-layer interaction losses, stabilizes the terminal normal shock under off-design conditions, and improves pressure recovery at elevated Mach numbers. The bleed-enabled compact configuration attains pressure-recovery levels comparable to those of a larger intake sized directly for Mach 1.9. These results indicate that bleed integration can extend the usable operating envelope of a compact intake, reducing the need to size external-compression intakes solely for the maximum flight Mach number.