FLIGHT INVESTIGATION OF LEADING EDGE SUCTION BOUNDARY LAYER CONTROL ON A LIAISON-TYPE STOL AIRCRAFT
Abstract
Leading edge boundary layer control has been studied on a modified YL-24, Helio Courier liaison airplane. The original leading edge slats were removed from one wing panel of the test airplane and instead, a fiberglas nose was installed accommodating leading edge suction BLC through perforations. By this asymmetrical configuration, a direct comparison was possible between the leading edge slat and leading edge BLC. Results of this investigation have shown that the leading edge BLC produced the same increment in maximum lift as the slat. The BLC wing, however, demonstrated 35 per cent lower profile drag in cruising flight. Effects of the leading edge suction were manifested in delayed transition and reduced growth of the boundary layer in the low speed flight regime. The practical application of leading edge boundary layer control seems to be most feasible as a supplementary device together with distributed suction BLC system for very high lift STOL airplanes. It may find application, however, as an alternative to leading edge slats or as a high lift device to prevent tip stall. Some fundamental design aspects are outlined. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 14, 1961
- Accession Number
- AD0251120
Entities
People
- Dezso Gyorgyfalvy
Organizations
- Mississippi State University