Accession Number:

AD0724723

Title:

Vortex Induced Rolling Moments on Cruciform Missiles at High Angle of Attack

Descriptive Note:

Corporate Author:

BOSTON UNIV MA ENGINEERING LABS

Personal Author(s):

Report Date:

1971-03-01

Pagination or Media Count:

64.0

Abstract:

The problem of predicting the induced roll phenomena associated with finned missiles at high angles of attack has been approached by examining the interaction between the body wake vortex system and the finned surfaces of the missile. The application of the classic Blasius moment integral to this problem permits the independent evaluation of each singularity in the flow field which may contribute to the moments. This method is applicable to missiles employing fin schemes of any geometry and is used herein to analyze the induced roll of a typical cruciform missile configuration. A computer program has been developed to generate numerical solutions utilizing those parameters which affect the magnitude and direction of the induced roll.

Subject Categories:

  • Rockets
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE