Static Aerodynamic Stability Characteristics of Bodies of Revolution with Wraparound Fins at Mach Numbers from 1.6 to 2.86,
Abstract
Wayne ;Craft,J. C. ;RD-TM-72-14AMCDR-1009*Guided missiles, *Fins, Aerodynamic stability, Aerodynamic forces, Pitch(Motion), Roll, Yaw, Angle of attackExperimental aerodynamic investigations were conducted in the NASA Langley Unitary Plan wind tunnel for several wraparound fins with straight and with swept leading edge mounted on bodies of revolution. Mach number ranged from 1.6 to 2.86 while angle of attack was varied from -6 degrees to 6 degrees at 0 degrees sideslip angle. Six component aerodynamic force and moment data were recorded on the complete missile configuration while simultaneously recording the aerodynamic normal force and bending moments acting on each fin. The results of these tests are presented herein in plotted form. The number designation given the test is UPWT 980. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1972
- Accession Number
- AD0772661
Entities
People
- C. Wayne Dahlke
- J. C. Craft
- John E. Vaughn
Organizations
- United States Army Aviation and Missile Command