Prediction of Forces and Moments on Finned Missiles at High Angle of Attack in Transonic Flow
Abstract
This report describes a theoretical investigation for the prediction of fin forces and moments on missiles at high angle of attack in subsonic and transonic flow. The body is assumed to be a circular cylinder with cruciform fins (or wings) as attached lifting surfaces. The theory considers a lifting surface of arbitrary planform; the leading edge can have arbitrary sweep back and the trailing edge can be swept back or forward. The missile can have an arbitrary roll (or bank) angle and each fin can have individual control deflection. The angle of attack of the missile is assumed to be such that the body vortex wake is symmetric. Extensive comparisons are made between predicted results and experimental measurements. Included in the comparisons are: panel normal force, root bending moment, induced roll moment, nonlinear roll damping moment, pitch (or yaw) control forces, and roll control moment. A computer program was written to implement the present method.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1980
- Accession Number
- ADA103964
Entities
People
- William L. Oberkampf
Organizations
- University of Texas at Austin