The Lockheed F-104 supersonic fighter, as shown in the figure, is the first fighter designed for sustained flight at Mach 2. The F-104 embodies good supersonic aircraft design. The airfoil thickness is 3.4%, and the plane area of the wing is 18.21 m2. The F-104, for example, flies steadily level at Mach 2 at an altitude of 11 km. The aircraft has a combat weight of 9400 kg. Assume that all of the aircraft’s lift comes from the wings (ignoring the fuselage and tail lift). What is the angle of attack of the wing relative to the free flow when the flight Mach number is 2 at the altitude of 11 km?

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ECD 1000