Aerodynamic Characteristic of the A3 DRDC-ISL Reference Projectile: Missile with Lattice Fins
Abstract
Free-flight tests were conducted in the Defence R&D Canada (DRDC) Valcartier aeroballistic range and at the ISL open range test site, and wind tunnel experiments in the DRDC Valcartier Indraft Trisonic, and the French-German Research Institute wind tunnels, as well as numerical computations on the A3 DRDC-ISL reference projectile at subsonic and supersonic velocities. The projectile consisted of an ogive-cylinder body with a length-to-diameter ratio of 10 with four lattice control surfaces. The reference grid fin consisted of nine thick cells in a vertical orientation and located at 0.7 cal from the base. The wind tunnel tests were conducted for various fin deflection angles at a range of angles of attack and roll orientations to determine the static aerodynamic coefficients. Very thin walls, an open base concept as well as a cruciform cell orientation, were also investigated in the wind tunnels. Flow visualizations were obtained from wind tunnel as well as free-flight tests. The wind tunnel tests were conducted in the Mach number range of 0.6 to 4.0, while the free-flight tests were conducted in the Mach number range of 1.4 to 3.3. The stability derivatives and static aerodynamic coefficients were very well determined. Numerical investigations were carried out on the reference configuration to visualize the flow features and obtain predictions of the aerodynamic coefficients. The aerodynamic coefficients and stability derivatives are presented individually and then compared where warranted. Finally, the results are compared with a classical fin design.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 12, 2005
- Accession Number
- ADA457243
Entities
People
- A. Bernier
- A. Dupuis
- C. Berner