Abstract
Thrust vectoring can provide fighter with advantages regarding performance, survivability and detectability. Two types of fluidic control Convergent-Divergent nozzle thrust vector technology, which are Shock Vectoring controlling and Throat Shift, are numerically simulated and their performances are analyzed. A nozzle with fixed geometry from nozzle inlet to throat, and fixed length of divergent flap is researched. The relative position of the secondary injecting flow is fixed, and the injecting direction is always vertical to the nozzle main flow. The nozzle flow fields are obtained via CFD numerical simulation. It can be seen from the results that, Throat Shift method is suitable for the nozzle expansion ratio less than 1.5, and Shock Vectoring controlling method is contrary to Throat Shift method, which is suitable for the nozzle expansion ratio greater than 1.5. The Throat Shift method can restrict the nozzle mass flow besides thrust vectoring. The main influence of the secondary mass flow is the ratio of secondary total pressure to main flow total pressure.
| Original language | English |
|---|---|
| Pages (from-to) | 206-209 |
| Number of pages | 4 |
| Journal | Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica |
| Volume | 30 |
| Issue number | 2 |
| State | Published - Apr 2012 |
Keywords
- Convergent-divergent nozzle
- Expansion ratio
- Flow control
- Thrust vector