In-Flight Flow Visualization Results of the F-106B with a Vortex Flap
Abstract
Surface and off-surface flow visualization techniques were used to visualize the three-dimensional vortex flows on the F-106 aircraft with vortex flaps installed. Results at angles of attack between 9 degrees and 18 degrees and Mach numbers from 0.3 to 0.9 are presented. A smoke flow vapor screen technique was used to document leading-edge vortex paths and sizes, while an oil flow technique was employed to provide detailed information on reattachment and separation line locations and other flow details. Results were obtained for two vortex flap deflection angles, 30 degrees and 40 degrees. Flow visualization revealed the existence of a multiple vortex system that had not previously been seen in subscale tests or predicted for this configuration. The vortex flap generated a leading-edge vortex system that reattached near the flap hinge over a wide angle-of-attack range. In addition to the primary vortex, flow visualization revealed the presence of several distinct vortices that traced a path from the vortex flap and then over the wing. (47 figures, 14 refs.)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2003
- Accession Number
- ADA418997
Entities
People
- James B. Hallissy
- Jay M. Brandon
- John E. Lamar
- Philip W. Brown
Organizations
- National Aeronautics and Space Administration