Accession Number:

ADA125499

Title:

Supersonic and Subsonic Wind Tunnel Heat-Transfer Measurements in the Base Cavity Region of the Shuttle Solid Rocket Booster during Simulated Reentry.

Descriptive Note:

Final rept. 16-20 Aug 82,

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Personal Author(s):

• Hawkins,W. R.
• Nutt,K. W.

Report Date:

1982-09-01

Pagination or Media Count:

42.0

Abstract:

Tests were conducted on the aft section of the Space Shuttle Solid Rocket Booster at Mach numbers 3.75 and 0.5 at selected angles of attack from 90-180 deg simulating reentry attitudes. The tests wre conducted in the AEDC Supersonic Wind Tunnel A to obtain heat-transfer coefficients in the base cavity region. Author

Descriptors:

• *HEAT TRANSFER
• *REENTRY VEHICLES
• *SPACE SHUTTLES
• *BOOSTER ROCKET ENGINES
• *AERODYNAMIC HEATING
• CAVITIES
• ANGLE OF ATTACK
• COEFFICIENTS
• HEATING
• WIND TUNNEL TESTS
• MACH NUMBER
• FLIGHT SIMULATION
• SOLID PROPELLANT ROCKET ENGINES
• SUPERSONIC WIND TUNNELS
• SUBSONIC WIND TUNNELS

Subject Categories:

• Test Facilities, Equipment and Methods
• Thermodynamics
• Rocket Engines
• Unmanned Spacecraft
• Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE