Accession Number:

AD0742229

Title:

A Method for Eliminating the Magnus Instability of a Finned Missile

Descriptive Note:

Technical rept.

Corporate Author:

AIR FORCE ARMAMENT LAB EGLIN AFB FL

Personal Author(s):

Report Date:

1971-11-01

Pagination or Media Count:

66.0

Abstract:

Subsonic one-degree-of-freedom and three-degrees-of-freedom wind tunnel tests were performed to determine whether N-vanes attached to a spinning, statically stable missile would eliminate the Magnus instabilities which can occur at high spin rates. The clean configuration missile that was tested had a large precession limit cycle of about 35 degrees amplitude. With N-vanes at 15 degrees, it was possible to eliminate the precession limit cycle. With the N-vanes at -15 degrees, the precession limit cycle was eliminated, and a nutation limit cycle of 25 degrees was created. The motion of the missile with and without N-vanes was photographed with a high speed camera. The angular data obtained were fit using the WOBBLE computer program to obtain the coefficients of pitching moment, pitch damping moment, and Magnus moment.

Subject Categories:

  • Ammunition and Explosives
  • Ballistics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE