Experimental Static Stability Studies of Several Tactical Missile Configurations at Mach Numbers from 1.76 to 3.01
Abstract
An experimental investigation was conducted in the low supersonic Mach number regime to obtain generalized, systematic force and moment data on several tactical missile configurations. Aerodynamic characteristics were determined for a typical missile body and nine body-fin configurations. The aerodynamic loading on each fin was also obtained for the nine fin configurations in a cruciform arrangement at zero deflection. The test was conducted at Mach numbers of 1.76, 2.00, 2.50, and 3.01 and free-stream Reynolds numbers, based on model length, from 8.3 to 14.5 million. The angle-of-attack range was from -1 to 45 deg, and the roll angle range was from 0 to 90 deg. Results are presented to illustrate the effects of fin aspect ratio, planform shape, and planform area on the missile and fin aerodynamic characteristics.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1975
- Accession Number
- ADA009137
Entities
People
- E. Earl Lindsay
- J L Jordan
Organizations
- Arnold Engineering Development Complex