Possibilities of producing supersonic jets with shock tubes
Abstract
The five possible methods investigated were: without expansion, with expansion in a wave, with expansion in a divergent nozzle, or with expansion in a Laval nozzle after compression in a standing or reflected shock. The equations for calculating the flow in the exhaust cross section are described and limits in applicability are indicated for each method. Flow data are given for typical cases, calculated for thermally and calorically perfect gases.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- May 1974
- Bibcode:
- 1974STIN...7713377O
- Keywords:
-
- Jet Exhaust;
- Shock Tubes;
- Supersonic Jet Flow;
- Gas Expansion;
- Nozzle Flow;
- Nozzle Geometry;
- Fluid Mechanics and Heat Transfer