Abstract
Unstart boundary is one of the most important issues of supersonic inlets, and also the foundation of inlet protection control. To solve this problem, the steady internal flowfield of ramjet inlets at different boundary conditions was simulated and analyzed. Based on the simulation data, the tool of dimensional analysis was introduced to find the variable describing the unstart boundary in this paper. The dimensionless pressure ratios of inlets were analyzed. The flow similar conditions of two hypersonic inlets are discussed. The results show that the unstart boundary of supersonic inlets is mainly concerned with Mach number of freestream without considering the variation of angle of attack.
| Original language | English |
|---|---|
| Pages (from-to) | 269-272 |
| Number of pages | 4 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 28 |
| Issue number | 3 |
| State | Published - Jun 2007 |
| Externally published | Yes |
Keywords
- Boundary
- Inlet
- Protection control
- Ramjet
- Unstart
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