Accession Number:

ADA066594

Title:

The Effect of a Complete Spin Turbine on the Exhaust Flow-Field for a Tube-Launched Rocket

Descriptive Note:

Final rept. Jul 1977-Sep 1978

Corporate Author:

TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS

Personal Author(s):

• Sutter, Jr, Samuel J.

Report Date:

1979-01-01

Pagination or Media Count:

34.0

Abstract:

Unbalanced forces on tube launched rockets during launch caused by exhaust fluid flow in the launcher-rocket annular gap is a problem confronting tube-launched rocket system designers. One alternative considered to alleviate the adverse effects is to rotate the rocket about its center of gravity during the launch phase to average out small deviations in the flight path. The spin turbine is a possible alternative with which to increase the rockets angular momentum. Previous work considered a single vanes effect on the exhaust flow, a complete spin turbine effect on the exhaust flow, and a rocket nozzle equipped with a complete spin turbine exhausting into a cylindrical launch tube. The current program demonstrates a significant difference in the flow around an isolated single vane from that around a single vane of a complete spin turbine. Three vane heights are considered.

Descriptors:

• *EXHAUST PLUMES
• *FLOW FIELDS
• *ROCKET LAUNCHERS
• ANGULAR MOMENTUM
• EXHAUST NOZZLES
• FLIGHT PATHS
• FLUID FLOW
• GUIDE VANES
• MATHEMATICAL ANALYSIS
• SPIN STABILIZED ROCKETS
• STATIC PRESSURE
• TEST FACILITIES
• TURBINES

Subject Categories:

• Rockets
• Fluid Mechanics
• Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE