Accession Number:

AD0901789

Title:

Experimental Aerodynamic Characteristics of a Fluidic-Controlled, Antitank Missile with Wraparound Fins at Mach Numbers from 0.2 to 3.0. Volume I. Data Report.

Descriptive Note:

Technical rept.,

Corporate Author:

ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL AER OBALLISTICS DIRECTORATE

Personal Author(s):

Report Date:

1971-12-03

Pagination or Media Count:

105.0

Abstract:

Aerodynamic wind tunnel tests have been conducted on an antitank missile model that contained stabilizing, wraparound fins and two different control systems. The model body had a 2-caliber secant ogive nose on an 8-caliber cylindrical segment. Two sets of fins were used with either a sonic transverse jet control system or the fluidic-control system interdigitated between the fins. The model angle of attack was varied from positive 6 degrees to negative 6 degrees for freestream Mach numbers from 0.2 to 3.0. The purpose of the test was to obtain information concerning the mutual aerodynamic interaction effect on the fin control system. Static force and moment data, at various angles of attack, and also body pressure data, in the vicinity of the control system, are presented. Author

Subject Categories:

  • Fluidics and Fluerics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE