Accession Number:

ADA034522

Title:

An Exploratory Investigation on Reducing Supersonic Missile Drag by Fluid Injection into a Turbulent Boundary Layer

Descriptive Note:

Technical rept.

Corporate Author:

ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL AEROBALLISTICS DIRECTORATE

Personal Author(s):

Report Date:

1976-11-01

Pagination or Media Count:

55.0

Abstract:

To determine general effects of fluid injection into a turbulent boundary layer on missile drag and stabilizing forces at angle of attack, an exploratory investigation was made at Mach 1.63 and 2.2. The test model was a body of revolution 10-cal long with a 3-cal tangent ogive nose and stabilizing fins. The mass injection was simulated by nitrogen and injected into the boundary layer from a porous section just aft of the nose body junction. The porous section was varied in length from 0.5 to 1.5 cal. Angle of attack range varied from -3.5 deg to 19 deg.

Subject Categories:

  • Guided Missile Warheads and Fuzes

Distribution Statement:

APPROVED FOR PUBLIC RELEASE