Accession Number : ADA040860

Title :   An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4.

Descriptive Note : Technical rept.,

Corporate Author : REMTECH INC HUNTSVILLE ALA

Personal Author(s) : Dahlke,C Wayne

PDF Url : ADA040860

Report Date : May 1977

Pagination or Media Count : 188

Abstract : The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author)

Descriptors :   *Aerodynamic stability, *Bodies of revolution, Wind tunnel tests, Exhaust plumes, Guided missiles, Simulation, Boundary layer flow, Flow separation, Thrust, Wing body configurations, Flow visualization, Aerodynamic forces, Moments, Ground effect, Interference, Angle of attack

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces

Distribution Statement : APPROVED FOR PUBLIC RELEASE