Abstract
Pitch- and roll-damping test mechanisms were developed for obtaining stability characteristics of high fineness ratio missiles at angles of attack up to 90 deg. Wind-tunnel tests were conducted on two missile configurations at Mach numbers 0.22 through 2.5. Mechanism evaluation tests showed that strut interference was not appreciable. The pitch-damping derivatives were found to be highly nonlinear functions of angle of attack, and the roll-damping and Magnus characteristics were very nonlinear with spin rate'at high angles of attack and low Mach numbers. Large and erratic variations in side force and yawing moment with angle of attack and high autorotation characteristics also were found at the low Mach numbers.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
