Patent ID: 7641144

Claim:
An aircraft, comprising: a. an aircraft body comprising an airfoil extending along a first axis from a leading edge to a trailing edge, and having a thickness to chord ratio greater than about twenty-five percent; and b. a cross-flow propulsion mechanism transversely mounted in said aircraft body and positioned adjacent said trailing edge thereof, said cross-flow propulsion mechanism comprising: i. a housing defining an inlet extending above said airfoil, a rotor compartment, and an outlet, ii. said inlet positioned on said aircraft body to receive an inflow of air along a second axis, iii. a rotor mounted partially within said rotor compartment to extend outwardly from said housing and said airfoil for receiving airflow along said airfoil and rotating about a third axis that is substantially perpendicular to said second longitudinal axis; and iv. said outlet adapted to receive the airflow processed through said rotor and exhaust air along a fourth axis.