Experimental Investigation of Vortex-Tail Interaction on a 76/40 Degree Double-Delta Wing
Abstract
An experimental investigation was conducted to quantify the vortex-tail interaction on a 76/40 degree double delta wing model. The effects of different fillets at the wing/strake juncture, tail span wise positions, and angles of attack were evaluated. The vertical tails were instrumented with 28 fast response pressure transducers. Pressure time histories and frequency power spectral densities were analyzed for 35 configurations. Angle of attack was varied from -2 to 40 degrees, tunnel dynamic pressure was 26.74 psf and Reynolds number was 1.3 million. The results show a strong dependence on fillet geometry, tail position, transducer measurement location, and angle of attack on the magnitude and frequency of the tail response to the vortex forcing. In addition, a low frequency pulse was found that contained tremendous energy.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 22, 1999
- Accession Number
- ADA368657
Entities
People
- David B. Findlay
- Hugo A. Gonzalez
- Terence A. Ghee
Organizations
- Naval Air Warfare Center