Experimental Investigation of Wake Velocity Fluctuations Behind Stalled Wings at Reynolds Numbers up to 4.8 Million.
Abstract
A wind tunnel investigation was made of transient wake velocities behind three stalled wings with NACA 0012 airfoils and spans equal to test section width up to a maximum Reynolds number of 4.8 million. Two wings had constant chords of 6 inches and 3 inches and one was tapered with a root chord of 12 inches and a tip chord of 6 inches. Anemometer time-history data were recorded on tape for angles of attack of 16.2 degrees, 21.1 degrees, 25.8 degrees and 30.3 degrees, and were used to evaluate wake geometry, frequency and mean and perturbation velocities for the constant chord wings. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1973
- Accession Number
- AD0763468
Entities
People
- Robert F. Smiley