An Experimental Investigation of the Drag on a Circular Cylinder and Curved Shell in Transonic Flow
Abstract
This study was one in a series by the Air Force Flight Dynamics Laboratory in large turret aerodynamic research. The objective of the study was the reduction of transonic drag of a particular turret configuration by the addition of area rule fairings. Wind tunnel models were tested at transonic Mach numbers from 0.6 to 0.9. An internally mounted force balance and unsteady pressure transducers were used to measure the forces and pressure variations on the model. Fairings were place beside and aft of the turret in an effort to reduce the transonic turret drag. The least drag configuration was a single fairing mounted behind the turret. This design had as much as a 55% drag reduction from the bare turret. This model also created the smallest pressure fluctuations in a circular cavity in the side of the turret.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1975
- Accession Number
- ADA021874
Entities
People
- Steve Borah
Organizations
- Air Force Institute of Technology