INVESTIGATION OF SHORT SUPERSONIC NOZZLES (ISSLEDOVANIE KOROTKIKH SVERKHZVUKOVYKH SOPEL),
Abstract
The article demonstrates experimentally that in nozzle optimization it is more expedient to use nozzles with weak shocks and some overexpansion, obtained by increasing the nozzle contour curvature as compared to that of a truncated perfect nozzle. Tests were conducted with a series of two-dimensional nozzles with a constant contour profile but with various degrees of flow expansion. Measurements were made of the static pressure distribution along the wall of the nozzle supersonic section and of the total pressure at the nozzle exit. The experimentally determined thrust of the nozzle supersonic section with an increased contour curvature was compared with the calculated thrust of the supersonic section of truncated perfect nozzles with uniform characteristics. The obtained results indicate that there is a definite range of nozzle dimensions at which the nozzles with increased contour curvatures are more advantageous than the truncated perfect nozzles. In this case, the contour inclination angle in a nozzle with a shock at the exit cross-section is not equal to zero and the shock effect is small. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1967
- Accession Number
- AD0669526
Entities
People
- L. V. Gogish
Organizations
- National Air and Space Intelligence Center