A Preliminary Method for Calculating the Aerodynamic Characteristics of Cruciform Missiles to High Angles of Attack Including Effects of Roll Angle and Control Deflections
Abstract
A method is presented together with a computer program for calculating the forces and moments on the components of a cruciform missile: nose, canard section, afterbody, and tail section. The program utilizes a skeleton data base for the fin normal forces and center-of-pressure positions. These quantities were derived from a set of fins of varying aspect ratio and taper ratio tested on a body having a diameter equal to half the tail span. The data base, covering a range 0.8 < or = M at infinity < or = 3.0, is extended to arbitrary cruciform body-tail configurations or body-wing-tail configurations using analytical and empirical methods. Pitch, yaw, and roll control are included in the method as well as the effects of missile roll angle. Comparisons are made between the predictions of the computer program and experiment for fin forces and configuration forces and moments for body0tail and wing-body-tail combinations up to angles of attack of 45 deg. On the whole acceptable agreement between prediction and experiment is obtained.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1977
- Accession Number
- ADA054349
Entities
People
- Charles A. Smith
- Jack N. Nielsen
- Michael J. Hemsch
Organizations
- Nielsen Engineering & Research (United States)