Accession Number : AD0771352

Title :   Analysis of the Linear Pitching and Yawing Motion of Curved-Finned Missiles

Descriptive Note : Technical rept.

Corporate Author : NAVAL WEAPONS LAB DAHLGREN VA

Personal Author(s) : Stevens, Frank L

PDF Url : AD0771352

Report Date : Oct 1973

Pagination or Media Count : 43

Abstract : Maple-Synge theory is used to establish the analytical form of the aerodynamic forces and moments acting on a four-finned, curved-finned vehicle. The linearized equations of motion are solved, and the effects of the curved- finned aerodynamics on the stability of motion are investigated. It is shown that small and moderate values of yawing moment due to angle-of-attack, characteristic of curved-finned configurations, can have significant effects on both transient and steady-state stability.

Descriptors :   *AERODYNAMIC CHARACTERISTICS, *FIN STABILIZED AMMUNITION, *FINS, AERODYNAMIC CONTROL SURFACES, ANGLE OF ATTACK, EQUATIONS OF MOTION, NUMERICAL ANALYSIS, PITCH(MOTION), YAW

Subject Categories : Ammunition and Explosives
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE