Analysis of the Linear Pitching and Yawing Motion of Curved-finned Missiles

Maple-Synge theory is used to establish the analytical form of the aerodynamic forces and moments acting on a four-finned, curved-finned vehicle. The linearized equations of motion are solved, and the effects of the curved-finned aerodynamics on the stability of motion are investigated. It is shown that small and moderate values of yawing moment due to angle-of-attack, characteristic of curved-finned configurations, can have significant effects on both transient and steady-state stability. Reproduced by NATIONAL TECHNICAL INFORMATION SERVICE u 5 ^ r . H ° v * s ° TM FORM I 4 7 O 1 N O v I " T # 0102-014-6700 ( P A G E 1 ) I ' S e c u r i t y C l a s s i f i c a ' JJNC1AS.SJJLLFD NWL Technical Report No. TR-2989 October 1973 ANALYSIS OF THE LINEAR PITCHING AND YAWING MOTION OF CURVED-FINNED MISSILES by Frank L. Stevens Warfare Analysis Department y r Approved for Public Release; Distribution Unlimited la. FOREWORD This report constitutes the first phase of a study to define the flight performance and stability characteristics of air-launched, curved-finned rockets. This work was performed under AIRTASK A3203200/009B/3F32-323-201. This report was reviewed by Dr. T. A. Clare, Head, Flight Dynamics Group and R. D. Cuddy, Head, Aeroballistics Division.