Subsonic Wind Tunnel Investigation of the High Lift Capability of a Circulation Control Wing on a 1/5-Scale T-2C Aircraft Model.

摘要

A circulation control wing,formed by the deflection of a 15% chord flap through 180degrees to produce a circular cylinder trailing edge with tangential upper surface blowing,was applied to a 1/5-scale T-2C aircraft model. The flap span/wing span ratio was 0.495,consistent with the conventional aircraft. Subsonic investigations were conducted in the Naval Ship Research and Development Center (NSRDC) 8-by 10-foot North Wind Tunnel over a dynamic pressure range of 5to 41 psf (Reynolds number based on mean aerodynamic chord of 0.60to 1.68million). Flap deflection was varied from 0to 180degrees,thus comparing the configurations of blown flap (moderate-to-high lift and lower drag for take-off) and the circular Coanda trailing edge (high lift and high drag for landing). (Modified author abstract)