A Wind Tunnel Study of the Effects of a Close-Coupled Canard on the Aerodynamic Characteristics of a Forward-Swept Wing in Incompressible Flow.
Abstract
Low speed wind tunnel tests and a boundary layer flow visualization study were conducted in the Air Force Institute of Technology fourteen inch wind tunnel to determine the differences in the aerodynamic characteristics among a forward-swept wing and several forward-swept wing/canard configurations. Both the wing and canard were constructed with an NACA 0006 airfoil section and had quarter chord sweeps of -30 and +40 deg, respectively. All tests were conducted at a dynamic pressure of 25.6 lbf/sg.ft and a Reynolds number of 1.9 x 100,000 based on the wing mean aerodynamic chord. The results show that the changes in the aerodynamic characteristics are dependent upon canard location relative to the wing, canard incidence, and model angle of attack. The largest increases in CL were observed for the two canard positions above and closest to the wing. A decrease in CM was noted as the canard location changed vertically from the upper to the lower test positions. An increase in CD occurred as the canard location approached the wing horizontally. Comparison of the force and moment data with the flow study photographs suggests that the canard wake/vortex system is responsible for the changes in the wing/canard aerodynamic characteristics.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1982
- Accession Number
- ADA124722
Entities
People
- Paul M. Weaver
Organizations
- Air Force Institute of Technology