Accession Number:

AD0832522

Title:

STUDY OF THE EFFECTS PRODUCED BY ASYMMETRICAL NOZZLE ENTRANCE GEOMETRIES ON THE DOWNSTREAM SUPERSONIC FLOW.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

• Thompson, Richard L.

Report Date:

1968-03-01

Pagination or Media Count:

51.0

Abstract:

Flow through a two-dimensional nozzle with asymmetrical entrance regions was studied using schlieren photographs and lateral-thrust versus chamber-pressure profiles. Lateral thrust was produced by asymmetrical flow separation and its magnitude was as much as twelve percent of the maximum axial thrust produced by the nozzle. Asymmetrical separation occurred at low pressures for both symmetrical and asymmetrical entrances, but the lateral-thrust profile was inconsistent for the symmetrical entrance. Inserts were used to obtain seven asymmetrical nozzle entrances which all affected the supersonic flow. Author

Descriptors:

• *AXISYMMETRIC FLOW
• SOLID PROPELLANT ROCKET ENGINES
• COMPRESSIBLE FLOW
• SUPERSONIC NOZZLES
• THRUST
• PRESSURE
• FLOW SEPARATION
• ASYMMETRY
• BODIES
• FLOW VISUALIZATION
• THESES
• TWO DIMENSIONAL FLOW
• NOZZLE INSERTS

Subject Categories:

• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE