Accession Number:

AD0855156

Title:

An Experimental Investigation at Supersonic Mach Numbers of Base Drag of Various Boattail Shapes with Simulated Base Rocket Exhaust.

Descriptive Note:

Memorandum rept.,

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1969-06-01

Pagination or Media Count:

45.0

Abstract:

An experimental investigation was conducted to determine the effect of boattail geometry and simulated base rocket nozzle flow on overall base drag. All tests were performed at Mach numbers 2.50, 3.00 and 3.50. Reasonable prediction of base drag for the reported boattail shapes can be made by using approximate and empirical equations. A conical boattail produced less drag than the other boattail shapes investigated. The maximum nozzle stagnation to free- stream pressure ratio reported is 315. Author

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE