Supersonic Stability and Control Characteristics of a Cruciform Missile Model with Delta Wings and Aft Tail Fin Controls.
Abstract
An investigation has been conducted to determine the static stability and control characteristics of a cruciform missile configuration with delta wings and aft tail fin controls. The tests were conducted in the Langley Unitary Plan wind tunnel at Mach numbers from 1.60 to 4.63 through an angle-of-attack range of -4 degree to 30 degree. Model roll orientation was varied from 0 degree to 135 degree. The results indicated good longitudinal stability and control characteristics throughout the test Mach number range. Relatively high induced rolling and yawing moments were apparent at asymmetric model roll angles for the lower test Mach numbers; however, sufficient roll and yaw control was available to trim to relatively high angles of attack and lift coefficients. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1979
- Accession Number
- ADA078611
Entities
People
- William A. Corlett
Organizations
- National Aeronautics and Space Administration