Patent ID: 6138946
Filing Date: 2000-10-31
Classification: B64C,B64D

Abstract:
An aircraft for subsonic speed having a fuselage and a turbofan drive engine in said fuselage comprising:an airflow inlet duct within said fuselage directing airflow into the turbofan of said engine,an outlet duct having an interior surface within said fuselage directing airflow from said turbofan,said fuselage having a longitudinal axis along the length of said fuselage,said inlet duct having an interior surface inside said fuselage and inclined to said longitudinal axis, with a larger opening coinciding with the front contour of said fuselage having a maximum cross-section of the periphery of said fuselage, and reducing in bore rearwards so that the lower generatrix of said inlet duct coincides with the lower surface of said fuselage and the upper generatrix of said inlet duct forms an acute angle with said longitudinal axis, whereby the narrowest end of said inlet duct discharges into the input of said turbofan;said interior surface of said inlet duct and said interior surface of said outlet duct producing lift from impact air during flight;said turbofan discharges said airflow through said rear outlet duct with the rear end of said outlet duct curved slightly downward, andwings attached to said fuselage which provide stability to said aircraft.