A 3 degree of freedom computer simulation was used to study a new configuration of the 2.75 inch Folding Fin Aircraft Rocket (FFAR) designed to carry the payload for the REFS (Rocket Electric Field Sounding) program. Since the shell of the payload section of the new configuration spins at a different rate than the motor casing, relatively large moments from the Magnus forces have some effect on the aerodynamic characteristics of the missile. Aerodynamic coefficients were based on existing flight data of the FFAR and predictions of the USAF Missile DATCOM program.
Effects of Magnus Moments on Missile Aerodynamic Performance
1991
38 pages
Report
Keine Angabe
Englisch
Missile Trajectories & Reentry Dynamics , Aerodynamics , Magnus effect , Aerodynamic characteristics , Guided missiles , Sounding rockets , Euler angles , Aircraft , Rockets , Payload , Coefficients , Computerized simulation , Predictions , Manned spacecraft , Velocity , Electric fields , Computer programs , Moments , Aerodynamic forces , Cylindrical bodies , Degrees of freedom , 3 Degree of Freedom , FFAR(Folding Fin Aircraft Rocket) , REFS(Rocket Electric Field Sounding) , USAF Missile DATCOM Program
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