Experimental Study of Induced Drag and Leading Edge Tangential Suction Force Spanwise Distribution of Thin Plane Delta Wings at Low Speeds Including the Effects of Fuselage Diameter.
Abstract
The spanwise distribution of the leading edge tangential suction forces along the leading edge of a thin 60 deg delta wing has been obtained by means of a novel experimental method. This method is based on measurements of the pressure at the apex of the leading edge at various spanwise stations. The tests were carried out in a low speed wind tunnel, and also the total forces and moments were recorded. The delta wing was tested alone and in combination with two schematic fuselages of different diameters. It was found that the presence of a fuselage reduces the leading edge suction in the vicinity of the fuselage, but slightly increases the suction near the wing tips. Another effect of the fuselage was to reduce the lift curve slope and the span efficiency factor. The effects were small for the smaller fuselage of typical aircraft- proportions, but fairly pronounced (of the order of 20%) for the larger fuselage of typical missile proportions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1972
- Accession Number
- AD0905640
Entities
People
- Sven-olof Ridder
Organizations
- Royal Institute of Technology