Abstract
Many solid propellent motors use a set of scrafed reversal nozzles located on the forward of the motors to provide reversal thrust during staging. Because the gasdynamic contour of reversal nozzle is not smooth and has a step in supersonic flow region, a series of shocks and flows separation in boundary-layer exists in flowfield of reversal nozzle. The viscous flowfields in scrafed reversal nozzle are simulated based on Renolds-average unsteady Navier-Stokes equations, with time-dependent method, MacCormack explicit scheme and Baldwin-Lomax algebraical turbulent model. The pressure distributions obtained from computation are in good agreement with experimental data.
| Original language | English |
|---|---|
| Pages (from-to) | 24-28 |
| Number of pages | 5 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 17 |
| Issue number | 1 |
| State | Published - 1996 |
| Externally published | Yes |
Keywords
- Computational fluid dynamics
- Numerical simulation
- Thrust reversal
- Unconventional nozzle