Question

Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data: • Total Wing Area: 18.22 m2 • Aircraft Mass: 8,000 kg -Is supersonic linear theory valid for this flight regime? Explain your answer.

Answer 1

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