The Influence of Helicopter Tail Shape on Drag: An Aerodynamic Study Using a Low Speed Wind Tunnel.
Abstract
This thesis examines the effect of helicopter tail shape on drag using a low speed wind tunnel at the Naval Postgraduate School. A modification to the; Aeronautical Engineering Department's 3.5 ft x 5 ft. wind tunnel was made to update facilities and allow this work. Major R. Scott Mair worked simultaneously to study the effect of nose shape on drag, a result of the 2-man requirement for wind tunnel work. The existing external balance was replaced with an internal balance and a variable angle-of-attack support system was constructed as well. Quantitative data was collected with this balance, and qualitative information was obtained by tufting the models and visualizing the airflow. The equipment built was adequate with the exception of one component of the balance, which will require a new balance to be built. This single deficiency was significant enough to invalidate the output of the balance and as a result any quantitative discussion of how a helicopter's tail shape affects drag. Without this data the explanation of drag using flow visualization is also not practical.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1985
- Accession Number
- ADA156304
Entities
People
- C. L. Sargent
Organizations
- Naval Postgraduate School