Abstract
In order to simplify the design process and obtain satisfying performances, taking round-to-square and round-to-rectangle nozzles as example, the exiting design methods for complex 3-D nozzles were compared and evaluated. The start position of contour transition and the shape of the exit cross section were analyzed by numerical simulation. A direct method for 3-D contour design was presented and proved to be technically feasible after actual fabrication. Two design criteria were developed: 1) the start position should be as close as possible to the throat within the technological level; 2) the exit cross section should be as similar as possible to a square, and if applying rectangular outlet, the size of the broader side should be 1.5 times greater than the dimension of the narrower side.
| Original language | English |
|---|---|
| Pages (from-to) | 499-503+521 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 26 |
| Issue number | 6 |
| State | Published - Dec 2005 |
Keywords
- Contour design
- Numerical simulation
- Performance
- Rocket engine
- Three-dimensional nozzle
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